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Unformatted text preview: cen58933_ch12.qxd 9/9/2002 9:48 AM Page 605 CHAPTER R A D I AT I O N H E AT T R A N S F E R
n Chapter 11, we considered the fundamental aspects of radiation and the
radiation properties of surfaces. We are now in a position to consider
radiation exchange between two or more surfaces, which is the primary
quantity of interest in most radiation problems.
We start this chapter with a discussion of view factors and the rules associated with them. View factor expressions and charts for some common configurations are given, and the crossedstrings method is presented. We then
discuss radiation heat transfer, first between black surfaces and then between
nonblack surfaces using the radiation network approach. We continue with radiation shields and discuss the radiation effect on temperature measurements
and comfort. Finally, we consider gas radiation, and discuss the effective
emissivities and absorptivities of gas bodies of various shapes. We also discuss radiation exchange between the walls of combustion chambers and the
hightemperature emitting and absorbing combustion gases inside. I 12
CONTENTS
12–1 The View Factor 606
12–2 View Factor Relations 609
12–3 Radiation Heat Transfer:
Black Surfaces 620
12–4 Radiation Heat Transfer:
Diffuse, Gray Surfaces 623
12–5 Radiation Shields and
the Radiation Effect 635
12–6 Radiation Exchange
with Emitting and
Absorbing Gases 639
Topic of Special Interest:
Heat Transfer from
the Human Body 649 605 cen58933_ch12.qxd 9/9/2002 9:48 AM Page 606 606
HEAT TRANSFER 12–1 Surface 2
Surface 1
Surface 3 Point
source FIGURE 12–1
Radiation heat exchange between
surfaces depends on the orientation
of the surfaces relative to each other,
and this dependence on orientation is
accounted for by the view factor. θ2 n1 r θ1
d dA2 A2 21 dA1
A1 FIGURE 12–2
Geometry for the determination of the
view factor between two surfaces. THE VIEW FACTOR Radiation heat transfer between surfaces depends on the orientation of the
surfaces relative to each other as well as their radiation properties and temperatures, as illustrated in Figure 12–1. For example, a camper will make the
most use of a campfire on a cold night by standing as close to the fire as possible and by blocking as much of the radiation coming from the fire by turning her front to the fire instead of her side. Likewise, a person will maximize
the amount of solar radiation incident on him and take a sunbath by lying
down on his back instead of standing up on his feet.
To account for the effects of orientation on radiation heat transfer between
two surfaces, we define a new parameter called the view factor, which is a
purely geometric quantity and is independent of the surface properties and
temperature. It is also called the shape factor, configuration factor, and angle
factor. The view factor based on the assumption that the surfaces are diffuse
emitters and diffuse reflectors is called the diffuse view factor, and the view
factor based on the assumption that the surfaces are diffuse emitters but specular reflectors is called the specular view factor. In this book, we will consider
radiation exchange between diffuse surfaces only, and thus the term view factor will simply mean diffuse view factor.
The view factor from a surface i to a surface j is denoted by Fi → j or just Fij,
and is defined as
Fij n2 I the fraction of the radiation leaving surface i that strikes surface j directly The notation Fi → j is instructive for beginners, since it emphasizes that the
view factor is for radiation that travels from surface i to surface j. However,
this notation becomes rather awkward when it has to be used many times in a
problem. In such cases, it is convenient to replace it by its shorthand version Fij.
Therefore, the view factor F12 represents the fraction of radiation leaving
surface 1 that strikes surface 2 directly, and F21 represents the fraction of the
radiation leaving surface 2 that strikes surface 1 directly. Note that the radiation that strikes a surface does not need to be absorbed by that surface. Also,
radiation that strikes a surface after being reflected by other surfaces is not
considered in the evaluation of view factors.
To develop a general expression for the view factor, consider two differential surfaces dA1 and dA2 on two arbitrarily oriented surfaces A1 and A2, respectively, as shown in Figure 12–2. The distance between dA1 and dA2 is r,
and the angles between the normals of the surfaces and the line that connects
dA1 and dA2 are 1 and 2, respectively. Surface 1 emits and reflects radiation
diffusely in all directions with a constant intensity of I1, and the solid angle
subtended by dA2 when viewed by dA1 is d 21.
The rate at which radiation leaves dA1 in the direction of 1 is I1 cos 1dA1.
dA2 cos 2 /r 2, the portion of this radiation that strikes
Noting that d 21
dA2 is
·
Q d A1 → d A2 I1 cos 1dA1d 21 I1 cos 1dA1 dA2 cos
r2 2 (121) cen58933_ch12.qxd 9/9/2002 9:48 AM Page 607 607
CHAPTER 12 The total rate at which radiation leaves dA1 (via emission and reflection) in all
I1) times the surface area,
directions is the radiosity (which is J1
·
Q d A1 J1dA1 I1dA1 (122) Then the differential view factor dFd A1 → d A2, which is the fraction of radiation
leaving dA1 that strikes dA2 directly, becomes
·
Q dA1 → dA2
·
Q dFd A1 → d A2 cos 1 dA1 cos
r2 2 dA2 (123) The differential view factor dFd A2 → d A1 can be determined from Eq. 12–3 by
interchanging the subscripts 1 and 2.
The view factor from a differential area dA1 to a finite area A2 can be
determined from the fact that the fraction of radiation leaving dA1 that strikes
A2 is the sum of the fractions of radiation striking the differential areas dA2.
Therefore, the view factor Fd A1 → A2 is determined by integrating dFd A1 → d A2
over A2,
cos Fd A1 → A2 1 A2 cos
r2 2 dA2 (124) The total rate at which radiation leaves the entire A1 (via emission and reflection) in all directions is
·
Q A1 J1A1 I1A1 (125) The portion of this radiation that strikes dA2 is determined by considering the
radiation that leaves dA1 and strikes dA2 (given by Eq. 12–1), and integrating
it over A1,
·
Q A1 → d A2 A1 ·
Q d A1 I1 cos
→ d A2 1 A1 cos
r2 2 dA2 dA1 (126) Integration of this relation over A2 gives the radiation that strikes the entire A2,
·
Q A1 → A2 A2 ·
Q A1 I1 cos
→ d A2 r A2 A1 1 cos
2 2 dA1 dA2 (127) Dividing this by the total radiation leaving A1 (from Eq. 12–5) gives the fraction of radiation leaving A1 that strikes A2, which is the view factor FA1 → A2 (or
F12 for short),
F12 F A1 → A2 ·
Q A1 → A2
·
Q
A1 1
A1 cos
A2 A1 1 cos
r2 2 dA1 dA2 (128) The view factor F A2 → A1 is readily determined from Eq. 12–8 by interchanging
the subscripts 1 and 2,
F21 F A2 → A1 ·
Q A2 → A1
·
Q
A2 1
A2 cos
A2 A1 1 cos
r2 2 dA1dA2 (129) cen58933_ch12.qxd 9/9/2002 9:48 AM Page 608 608
HEAT TRANSFER Note that I1 is constant but r, 1, and 2 are variables. Also, integrations can be
performed in any order since the integration limits are constants. These relations confirm that the view factor between two surfaces depends on their relative orientation and the distance between them.
Combining Eqs. 12–8 and 12–9 after multiplying the former by A1 and the
latter by A2 gives 1
F1 → 1 = 0
(a) Plane surface A1F12 2
F2 → 2 = 0 A2F21 (1210) which is known as the reciprocity relation for view factors. It allows the calculation of a view factor from a knowledge of the other.
The view factor relations developed above are applicable to any two surfaces i and j provided that the surfaces are diffuse emitters and diffuse reflectors (so that the assumption of constant intensity is valid). For the special case
of j i, we have (b) Convex surface 3
F3 → 3 ≠ 0 Fi → i
(c) Concave surface FIGURE 12–3
The view factor from a surface
to itself is zero for plane or
convex surfaces and nonzero
for concave surfaces.
Outer
sphere
2 Inner
sphere
1 F1 → 2 = 1 FIGURE 12–4
In a geometry that consists of two
concentric spheres, the view factor
F1 → 2 1 since the entire radiation
leaving the surface of the smaller
sphere will be intercepted by the
larger sphere. the fraction of radiation leaving surface i that strikes itself directly Noting that in the absence of strong electromagnetic fields radiation beams
travel in straight paths, the view factor from a surface to itself will be zero unless the surface “sees” itself. Therefore, Fi → i 0 for plane or convex surfaces
and Fi → i 0 for concave surfaces, as illustrated in Figure 12–3.
The value of the view factor ranges between zero and one. The limiting case
Fi → j 0 indicates that the two surfaces do not have a direct view of each
other, and thus radiation leaving surface i cannot strike surface j directly. The
other limiting case Fi → j 1 indicates that surface j completely surrounds surface i, so that the entire radiation leaving surface i is intercepted by surface j.
For example, in a geometry consisting of two concentric spheres, the entire
radiation leaving the surface of the smaller sphere (surface 1) will strike the
larger sphere (surface 2), and thus F1 → 2 1, as illustrated in Figure 12–4.
The view factor has proven to be very useful in radiation analysis because it
allows us to express the fraction of radiation leaving a surface that strikes another surface in terms of the orientation of these two surfaces relative to each
other. The underlying assumption in this process is that the radiation a surface
receives from a source is directly proportional to the angle the surface subtends when viewed from the source. This would be the case only if the
radiation coming off the source is uniform in all directions throughout its
surface and the medium between the surfaces does not absorb, emit, or scatter
radiation. That is, it will be the case when the surfaces are isothermal and
diffuse emitters and reflectors and the surfaces are separated by a nonparticipating medium such as a vacuum or air.
The view factor F1 → 2 between two surfaces A1 and A2 can be determined in
a systematic manner first by expressing the view factor between two differential areas dA1 and dA2 in terms of the spatial variables and then by performing
the necessary integrations. However, this approach is not practical, since, even
for simple geometries, the resulting integrations are usually very complex and
difficult to perform.
View factors for hundreds of common geometries are evaluated and the results are given in analytical, graphical, and tabular form in several publications. View factors for selected geometries are given in Tables 12–1 and 12–2
in analytical form and in Figures 12–5 to 12–8 in graphical form. The view cen58933_ch12.qxd 9/9/2002 9:48 AM Page 609 609
CHAPTER 12 TABLE 12–1
View factor expressions for some common geometries of finite size (3D)
Geometry
Aligned parallel rectangles –2
–
– 2 1/2
–
2
Fi → j = —— ln (1 + X –)(1 +–Y—
—————— )
––
––
–
2 + Y2
πXY
1+X
–
–
–
–
– 2 1/ 2 –1
–
X
+ X(1 + Y ) tan ———–—
– 2 1/2
–
(1 + Y )
–
–
–
–
–
–
Y
+ Y(1 + X 2)1/ 2 tan–1 ———–—
– 2 1/2
–
(1 + X ) j
L
i Y Relation
–
–
–
–
X = X/L and Y = Y/L X –
–
––
––
–
–
– X tan–1 X – Y tan–1 Y Coaxial parallel disks
rj
j
ri L
i Perpendicular rectangles
with a common edge Ri = ri /L and Rj = rj /L
1 + R2
j
S = 1 + ——–
R2
i
rj
1
Fi → j = – S – S 2 – 4 —
2
ri () 2 1/ 2 H = Z /X and W = Y/X ( 1
1
1
Fi → j = —– W tan–1 — + H tan–1 —
πW
W
H
1
– (H 2 + W 2)1/ 2 tan–1 ———–——
(H 2 + W 2)1/2 j
Z i
Y X (1 + W 2)(1 + H 2)
+ 1 ln ———————
–
4
1 + W2 + H2
W 2(1 + W 2 + H 2)
× ————————
(1 + W 2)(W 2 + H 2) W2 H 2(1 + H 2 + W 2)
× ————————
(1 + H 2)(H 2 + W 2) H2 ) factors in Table 12–1 are for threedimensional geometries. The view factors
in Table 12–2, on the other hand, are for geometries that are infinitely long
in the direction perpendicular to the plane of the paper and are therefore
twodimensional. 12–2 I VIEW FACTOR RELATIONS Radiation analysis on an enclosure consisting of N surfaces requires the evaluation of N2 view factors, and this evaluation process is probably the most
timeconsuming part of a radiation analysis. However, it is neither practical
nor necessary to evaluate all of the view factors directly. Once a sufficient
number of view factors are available, the rest of them can be determined by
utilizing some fundamental relations for view factors, as discussed next. cen58933_ch12.qxd 9/9/2002 9:48 AM Page 610 610
HEAT TRANSFER TABLE 12–2
View factor expressions for some infinitely long (2D) geometries
Geometry Relation Parallel plates with midlines
connected by perpendicular line
wi Wi = wi /L and Wj = wj /L i [(Wi + Wj)2 + 4]1/ 2 – (Wj – Wi)2 + 4]1/ 2
Fi → j = ———————————————
2Wi L
j
wj
Inclined plates of equal width
and with a common edge
j 1
Fi → j = 1 – sin – α
2 w
α
i
w
Perpendicular plates with a common edge
j wj
wj
1
Fi → j = – 1 + — – 1 + —
2
wi
wi () wj 2 1/2 i wi
Threesided enclosure wk wj
k wi + wj – wk
Fi → j = —————
2wi j
i
wi Infinite plane and row of cylinders
s D
j ()
() D
Fi → j = 1 – 1 – —
s 2 1/ 2 s2 – D2
D
+ — tan–1 ———
s
D2 i 1/ 2 1 The Reciprocity Relation
The view factors Fi → j and Fj → i are not equal to each other unless the areas of
the two surfaces are. That is,
Fj → i
Fj → i Fi → j
Fi → j when
when Ai
Ai Aj
Aj cen58933_ch12.qxd 9/9/2002 9:48 AM Page 611 611
CHAPTER 12
1.0
0.9
0.8
0.7
0.6
0.5 L2
L1 10 5
43 A2 D 0.4 R A1 o
a ti /D
L1 2
1.5
1 0.9
0.8
0.7
0.6
0.5 0.3
10 0.2 0.4
0.3
0.25
0.2
0.18
0.16
0.14
0.12
0.1 F1 → 2
0.1
0.09
0.08
0.07
0.06
0.05 0.5
0.4 0.04 0.3 0.03 0.2 0.02
0.1 0.2 A2 0.3 L2 W
A1 0.4 0.5 0.6 0.8 1
2
Ratio L 2 / D 3 4 56 8 10 L1
0.1
0.15
0.2 0.4 20 Asymptote 0.01
0.1 FIGURE 12–5
View factor between two
aligned parallel rectangles of
equal size. 0.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
1.2
1.4
1.6
1.8
2.0
2.5
3 L 1 /W 0.3 Ra
tio F1 → 2
0.2 0.5
0.1 4
5
6
8
10
20 1
2 0
0.1 5 10
0.2
0.3 0.4 0.5 0.6 0.8 1 2
Ratio L2/W 3 4 56 8 10 20 FIGURE 12–6
View factor between two
perpendicular rectangles with
a common edge. cen58933_ch12.qxd 9/9/2002 9:48 AM Page 612 612
HEAT TRANSFER
1.0
0.9 r2 r2 / L = 8
6 2
5
4 0.8 L
r1 3
0.7 1
2 1.5 0.6
1.25 F1 → 2
0.5 1.0 0.4
0.3 0.8 0.2 0.6
0.5
0.4 0.1 FIGURE 12–7
View factor between two
coaxial parallel disks. 0
0.1 0.2 0.3 0.4 0.6 1.0
L /r1 r2 /L = 0.3
2 3 4 56 8 10 1.0
A2 L r1
0.8
r2
A1 1.0
0.9 0.6
= 0.8 L/ r
2 F2 → 1 2 0.7 L/ r
2 0.6 1 4 0. 5 0.4 0. 25 0.5
F2 → 2 2 1 0.4 1 0.3 0. 0.2 = 0.5 0.2 0.25 0.1
0
0 0.2 0.4 0.6
r1/r2 0.8 1.0 0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0
r1/r2 FIGURE 12–8
View factors for two concentric cylinders of finite length: (a) outer cylinder to inner cylinder; (b) outer cylinder to itself. cen58933_ch12.qxd 9/9/2002 9:48 AM Page 613 613
CHAPTER 12 We have shown earlier the pair of view factors Fi → j and Fj → i are related to
each other by
AiFi → j AjFj → i (1211) This relation is referred to as the reciprocity relation or the reciprocity rule,
and it enables us to determine the counterpart of a view factor from a knowledge of the view factor itself and the areas of the two surfaces. When determining the pair of view factors Fi → j and Fj → i, it makes sense to evaluate first
the easier one directly and then the more difficult one by applying the reciprocity relation. 2 The Summation Rule
The radiation analysis of a surface normally requires the consideration of the
radiation coming in or going out in all directions. Therefore, most radiation
problems encountered in practice involve enclosed spaces. When formulating
a radiation problem, we usually form an enclosure consisting of the surfaces
interacting radiatively. Even openings are treated as imaginary surfaces with
radiation properties equivalent to those of the opening.
The conservation of energy principle requires that the entire radiation leaving any surface i of an enclosure be intercepted by the surfaces of
the enclosure. Therefore, the sum of the view factors from surface i of an enclosure to all surfaces of the enclosure, including to itself, must equal unity.
This is known as the summation rule for an enclosure and is expressed as
(Fig. 12–9) Surface i N Fi → j 1 (1212) j1 where N is the number of surfaces of the enclosure. For example, applying the
summation rule to surface 1 of a threesurface enclosure yields
3 F1 → j F1 → 1 F1 → 2 F1 → 3 1 j1 The summation rule can be applied to each surface of an enclosure by varying i from 1 to N. Therefore, the summation rule applied to each of the N surfaces of an enclosure gives N relations for the determination of the view
factors. Also, the reciprocity rule gives 1 N(N 1) additional relations. Then
2
the total number of view factors that need to be evaluated directly for an
Nsurface enclosure becomes
N2 [N 1
N(N
2 1)] 1
N(N
2 1) For example, for a sixsurface enclosure, we need to determine only
1
36 view factors directly. The remaining
6(6
1)
15 of the 62
2
21 view factors can be determined from the 21 equations that are obtained by
applying the reciprocity and the summation rules. FIGURE 12–9
Radiation leaving any surface i of
an enclosure must be intercepted
completely by the surfaces of the
enclosure. Therefore, the sum of
the view factors from surface i to
each one of the surfaces of the
enclosure must be unity. cen58933_ch12.qxd 9/9/2002 9:48 AM Page 614 614
HEAT TRANSFER EXAMPLE 12–1 View Factors Associated with Two Concentric
Spheres Determine the view factors associated with an enclosure formed by two spheres,
shown in Figure 12–10. SOLUTION The view factors associated with two concentric spheres are to be r1
r2 1
2 FIGURE 12–10
The geometry considered
in Example 12–1. determined.
Assumptions The surfaces are diffuse emitters and reflectors.
Analysis The outer surface of the smaller sphere (surface 1) and inner surface
of the larger sphere (surface 2) form a twosurface enclosure. Therefore, N 2
and this enclosure involves N 2 22 4 view factors, which are F11, F12, F21,
and F22. In this twosurface enclosure, we need to determine only
1 N(N
2 1) 1
2 2(2 1) 1 view factor directly. The remaining three view factors can be determined by the
application of the summation and reciprocity rules. But it turns out that we can
determine not only one but two view factors directly in this case by a simple
inspection: F11
F12 0,
1, since no radiation leaving surface 1 strikes itself
since all radiation leaving surface 1 strikes surface 2 Actually it would be sufficient to determine only one of these view factors by
inspection, since we could always determine the other one from the summation
rule applied to surface 1 as F11 F12 1.
The view factor F21 is determined by applying the reciprocity relation to surfaces 1 and 2: A1F12 A2F21 which yields
A1
F
A2 12 F21 4 r12
4 r22 r1
r2 1 2 Finally, the view factor F22 is determined by applying the summation rule to surface 2: F21 F22 1 and thus F22 1 F21 1 r1
r2 2 Discussion Note that when the outer sphere is much larger than the inner
sphere (r2
r1), F22 approaches one. This is expected, since the fraction of
radiation leaving the outer sphere that is intercepted by the inner sphere will be
negligible in that case. Also note that the two spheres considered above do not
need to be concentric. However, the radiation analysis will be most accurate for
the case of concentric spheres, since the radiation is most likely to be uniform
on the surfaces in that case. cen58933_ch12.qxd 9/9/2002 9:48 AM Page 615 615
CHAPTER 12 3 The Superposition Rule
Sometimes the view factor associated with a given geometry is not available
in standard tables and charts. In such cases, it is desirable to express the given
geometry as the sum or difference of some geometries with known view factors, and then to apply the superposition rule, which can be expressed as the
view factor from a surface i to a surface j is equal to the sum of the view factors from surface i to the parts of surface j. Note that the reverse of this is not
true. That is, the view factor from a surface j to a surface i is not equal to the
sum of the view factors from the parts of surface j to surface i.
Consider the geometry in Figure 12–11, which is infinitely long in the
direction perpendicular to the plane of the paper. The radiation that leaves
surface 1 and strikes the combined surfaces 2 and 3 is equal to the sum of the
radiation that strikes surfaces 2 and 3. Therefore, the view factor from surface
1 to the combined surfaces of 2 and 3 is
F1 → (2, 3) F1 → 2 F1 → 3 (1213) Suppose we need to find the view factor F1 → 3. A quick check of the view factor expressions and charts in this section will reveal that such a view factor
cannot be evaluated directly. However, the view factor F1 → 3 can be determined from Eq. 12–13 after determining both F1 → 2 and F1 → (2, 3) from the
chart in Figure 12–12. Therefore, it may be possible to determine some difficult view factors with relative ease by expressing one or both of the areas as
the sum or differences of areas and then applying the superposition rule.
To obtain a relation for the view factor F(2, 3) → 1, we multiply Eq.
12–13 by A1,
A1 F1 → (2, 3) A1 F1 → 2 3 3
= 2 +
2 1 1 1 F1 → (2, 3) =F1 → 2 + F1 → 3 FIGURE 12–11
The view factor from a surface to a
composite surface is equal to the sum
of the view factors from the surface to
the parts of the composite surface.
3 r2 = 5 cm
r3 = 8 cm 2 A1 F1 → 3 and apply the reciprocity relation to each term to get
(A2 A3)F(2, 3) → 1 A2 F2 → 1 A3 F3 → 1 or
F(2, 3) → 1 A2 F2 → 1
A2 A3 F3 → 1
A3 (1214) Areas that are expressed as the sum of more than two parts can be handled in
a similar manner. EXAMPLE 12–2 Fraction of Radiation Leaving
through an Opening Determine the fraction of the radiation leaving the base of the cylindrical enclosure shown in Figure 12–12 that escapes through a coaxial ring opening
at its top surface. The radius and the length of the enclosure are r1
10 cm
and L
10 cm, while the inner and outer radii of the ring are r2
5 cm and
r3 8 cm, respectively. 1 r1 = 10 cm FIGURE 12–12
The cylindrical enclosure
considered in Example 12–2. cen58933_ch12.qxd 9/9/2002 9:48 AM Page 616 616
HEAT TRANSFER SOLUTION The fraction of radiation leaving the base of a cylindrical enclosure
through a coaxial ring opening at its top surface is to be determined.
Assumptions The base surface is a diffuse emitter and reflector.
Analysis We are asked to determine the fraction of the radiation leaving the
base of the enclosure that escapes through an opening at the top surface.
Actually, what we are asked to determine is simply the view factor F1 → ring from
the base of the enclosure to the ringshaped surface at the top.
We do not have an analytical expression or chart for view factors between a
circular area and a coaxial ring, and so we cannot determine F1 → ring directly.
However, we do have a chart for view factors between two coaxial parallel disks,
and we can always express a ring in terms of disks.
Let the base surface of radius r1 10 cm be surface 1, the circular area of
r2
5 cm at the top be surface 2, and the circular area of r3
8 cm be surface 3. Using the superposition rule, the view factor from surface 1 to surface 3
can be expressed as
F1 → 3 F1 → 2 F1 → ring since surface 3 is the sum of surface 2 and the ring area. The view factors F1 → 2
and F1 → 3 are determined from the chart in Figure 12–7. L
r1
L
r1 10 cm
10 cm
10 cm
10 cm 1 and 1 and r2
L
r3
L 5 cm
10 cm
8 cm
10 cm (Fig. 12–7) 0.5 → 0.8 → (Fig. 12–7) F1 → 2 0.11 F1 → 3 0.28 Therefore, F1 → ring F1 → 3 F1 → 2 0.28 0.11 0.17 which is the desired result. Note that F1 → 2 and F1 → 3 represent the fractions of
radiation leaving the base that strike the circular surfaces 2 and 3, respectively,
and their difference gives the fraction that strikes the ring area. 4 The Symmetry Rule
3
2
1 F1 → 2 = F1 → 3
(Also, F2 → 1 = F3 → 1 ) FIGURE 12–13
Two surfaces that are symmetric about
a third surface will have the same
view factor from the third surface. The determination of the view factors in a problem can be simplified further
if the geometry involved possesses some sort of symmetry. Therefore, it is
good practice to check for the presence of any symmetry in a problem before
attempting to determine the view factors directly. The presence of symmetry
can be determined by inspection, keeping the definition of the view factor in
mind. Identical surfaces that are oriented in an identical manner with respect
to another surface will intercept identical amounts of radiation leaving that
surface. Therefore, the symmetry rule can be expressed as two (or more) surfaces that possess symmetry about a third surface will have identical view factors from that surface (Fig. 12–13).
The symmetry rule can also be expressed as if the surfaces j and k are symmetric about the surface i then Fi → j Fi → k. Using the reciprocity rule, we
can show that the relation Fj → i Fk → i is also true in this case. cen58933_ch12.qxd 9/9/2002 9:48 AM Page 617 617
CHAPTER 12 EXAMPLE 12–3 View Factors Associated with a Tetragon Determine the view factors from the base of the pyramid shown in Figure 12–14
to each of its four side surfaces. The base of the pyramid is a square, and its
side surfaces are isosceles triangles. 3
4
2
5 SOLUTION The view factors from the base of a pyramid to each of its four side
surfaces for the case of a square base are to be determined.
Assumptions The surfaces are diffuse emitters and reflectors.
Analysis The base of the pyramid (surface 1) and its four side surfaces (surfaces 2, 3, 4, and 5) form a fivesurface enclosure. The first thing we notice
about this enclosure is its symmetry. The four side surfaces are symmetric
about the base surface. Then, from the symmetry rule, we have F12 F13 F14 1 FIGURE 12–14
The pyramid considered
in Example 12–3. F15 Also, the summation rule applied to surface 1 yields
5 F1j
j However, F11
above yield F11 F12 F13 F14 F15 1 1 0, since the base is a flat surface. Then the two relations F12 F13 F14 F15 0.25 Discussion Note that each of the four side surfaces of the pyramid receive
onefourth of the entire radiation leaving the base surface, as expected. Also
note that the presence of symmetry greatly simplified the determination of the
view factors. EXAMPLE 12–4 View Factors Associated with a Triangular Duct Determine the view factor from any one side to any other side of the infinitely
long triangular duct whose cross section is given in Figure 12–15. SOLUTION The view factors associated with an infinitely long triangular duct
are to be determined.
Assumptions The surfaces are diffuse emitters and reflectors.
Analysis The widths of the sides of the triangular cross section of the duct are
L1, L2, and L3, and the surface areas corresponding to them are A1, A2, and A3,
respectively. Since the duct is infinitely long, the fraction of radiation leaving
any surface that escapes through the ends of the duct is negligible. Therefore,
the infinitely long duct can be considered to be a threesurface enclosure,
N 3.
This enclosure involves N 2 32 9 view factors, and we need to determine
1
N(N
2 1) 1
2 3(3 1) 3 3 2 L3 L2 1 L1 FIGURE 12–15
The infinitely long triangular duct
considered in Example 12–4. cen58933_ch12.qxd 9/9/2002 9:48 AM Page 618 618
HEAT TRANSFER of these view factors directly. Fortunately, we can determine all three of them by
inspection to be F11 F22 F33 0 since all three surfaces are flat. The remaining six view factors can be determined by the application of the summation and reciprocity rules.
Applying the summation rule to each of the three surfaces gives F11
F21
F31 F12
F22
F32 F13
F23
F33 1
1
1 Noting that F11
F22
F33
0 and multiplying the first equation by A1, the
second by A2, and the third by A3 gives A1F12
A2F21
A3F31 A1F13
A2F23
A3F32 A1
A2
A3 Finally, applying the three reciprocity relations A1F12
and A2F23 A3F32 gives A1F12
A1F12
A1F13 A1F13
A2F23
A2F23 A2F21, A1F13 A3F31, A1
A2
A3 This is a set of three algebraic equations with three unknowns, which can be
solved to obtain F12
F13
F23 A1
A1
A2 A2
2A1
A3
2A1 A3 L1 A2 L1 A3
2A2 A1 L2 L2
2L1
L3
2L1
L3
2L2 L3
L2
L1 (1215) Discussion Note that we have replaced the areas of the side surfaces by their
corresponding widths for simplicity, since A Ls and the length s can be factored out and canceled. We can generalize this result as the view factor from a
surface of a very long triangular duct to another surface is equal to the sum of
the widths of these two surfaces minus the width of the third surface, divided
by twice the width of the first surface. View Factors between Infinitely Long Surfaces:
The CrossedStrings Method
Many problems encountered in practice involve geometries of constant cross
section such as channels and ducts that are very long in one direction relative cen58933_ch12.qxd 9/9/2002 9:48 AM Page 619 619
CHAPTER 12 to the other directions. Such geometries can conveniently be considered to be
twodimensional, since any radiation interaction through their end surfaces
will be negligible. These geometries can subsequently be modeled as being
infinitely long, and the view factor between their surfaces can be determined
by the amazingly simple crossedstrings method developed by H. C. Hottel in
the 1950s. The surfaces of the geometry do not need to be flat; they can be
convex, concave, or any irregular shape.
To demonstrate this method, consider the geometry shown in Figure 12–16,
and let us try to find the view factor F1 → 2 between surfaces 1 and 2. The first
thing we do is identify the endpoints of the surfaces (the points A, B, C, and D)
and connect them to each other with tightly stretched strings, which are
indicated by dashed lines. Hottel has shown that the view factor F1 → 2 can be
expressed in terms of the lengths of these stretched strings, which are straight
lines, as
F1 → 2 (L5 L6) (L3
2L1 L4) (1216) 2
L2 C D
L5 L6
L4 L3 L1 B A 1 FIGURE 12–16
Determination of the view factor
F1 → 2 by the application of
the crossedstrings method. Note that L5 L6 is the sum of the lengths of the crossed strings, and L3 L4
is the sum of the lengths of the uncrossed strings attached to the endpoints.
Therefore, Hottel’s crossedstrings method can be expressed verbally as
Fi → j (Crossed strings)
(Uncrossed strings)
2 (String on surface i) (1217) The crossedstrings method is applicable even when the two surfaces considered share a common edge, as in a triangle. In such cases, the common edge
can be treated as an imaginary string of zero length. The method can also be
applied to surfaces that are partially blocked by other surfaces by allowing the
strings to bend around the blocking surfaces. EXAMPLE 12–5 The CrossedStrings Method for View Factors Two infinitely long parallel plates of widths a
12 cm and b
5 cm are located a distance c 6 cm apart, as shown in Figure 12–17. (a) Determine the
view factor F1 → 2 from surface 1 to surface 2 by using the crossedstrings
method. (b) Derive the crossedstrings formula by forming triangles on the given
geometry and using Eq. 12–15 for view factors between the sides of triangles. SOLUTION The view factors between two infinitely long parallel plates are to
be determined using the crossedstrings method, and the formula for the view
factor is to be derived.
Assumptions The surfaces are diffuse emitters and reflectors.
Analysis (a) First we label the endpoints of both surfaces and draw straight
dashed lines between the endpoints, as shown in Figure 12–17. Then we identify the crossed and uncrossed strings and apply the crossedstrings method
(Eq. 12–17) to determine the view factor F1 2: F1 → 2 (Crossed strings)
(Uncrossed strings)
2 (String on surface 1) (L5 L6) (L3
2L1 L4) b = L 2 = 5 cm
C 2 D L4 L3
c = 6 cm
A L5 L6 1
a = L 1 = 12 cm B FIGURE 12–17
The two infinitely long parallel
plates considered in Example 12–5. cen58933_ch12.qxd 9/9/2002 9:48 AM Page 620 620
HEAT TRANSFER where L1
L2
L3 a
b
c 12 cm
5 cm
6 cm L4
L5
L6 72 62 9.22 cm
52 62 7.81 cm
122 62 13.42 cm Substituting, [(7.81 F1 → 2 13.42) (6 9.22)] cm
2 12 cm 0.250 (b) The geometry is infinitely long in the direction perpendicular to the plane of
the paper, and thus the two plates (surfaces 1 and 2) and the two openings
(imaginary surfaces 3 and 4) form a foursurface enclosure. Then applying the
summation rule to surface 1 yields F11
But F11 F12 F13 F14 1 0 since it is a flat surface. Therefore, F12 1 F13 F14 where the view factors F13 and F14 can be determined by considering the triangles ABC and ABD, respectively, and applying Eq. 12–15 for view factors between the sides of triangles. We obtain F13 L1 L3
2L1 L6
, L1 F14 L4
2L1 L5 Substituting, F12 1
(L5 L1 L3
2L1 L6) (L3
2L1 L6 L1 L4
2L1 L5 L4) which is the desired result. This is also a miniproof of the crossedstrings
method for the case of two infinitely long plain parallel surfaces. 12–3 I RADIATION HEAT TRANSFER:
BLACK SURFACES So far, we have considered the nature of radiation, the radiation properties of
materials, and the view factors, and we are now in a position to consider the
rate of heat transfer between surfaces by radiation. The analysis of radiation
exchange between surfaces, in general, is complicated because of reflection: a
radiation beam leaving a surface may be reflected several times, with partial
reflection occurring at each surface, before it is completely absorbed. The
analysis is simplified greatly when the surfaces involved can be approximated cen58933_ch12.qxd 9/9/2002 9:48 AM Page 621 621
CHAPTER 12 as blackbodies because of the absence of reflection. In this section, we consider radiation exchange between black surfaces only; we will extend the
analysis to reflecting surfaces in the next section.
Consider two black surfaces of arbitrary shape maintained at uniform temperatures T1 and T2, as shown in Figure 12–18. Recognizing that radiation
T 4 per unit surface area and that the
leaves a black surface at a rate of Eb
view factor F1 → 2 represents the fraction of radiation leaving surface 1 that
strikes surface 2, the net rate of radiation heat transfer from surface 1 to surface 2 can be expressed as
Radiation leaving
Radiation leaving
the entire surface 1
the entire surface 2
that strikes surface 2
that strikes surface 1
A1 Eb1 F1 → 2 A2 Eb2 F2 → 1
(W) ·
Q1 → 2 Applying the reciprocity relation A1F1 → 2
·
Q1 → 2 A1 F1 → 2 (T14 T2
A2
·
Q12 T1
A1 2
1 (1218) FIGURE 12–18
Two general black surfaces maintained
at uniform temperatures T1 and T2. A2F2 → 1 yields
T24) (W) (1219) ·
which is the desired relation. A negative value for Q 1 → 2 indicates that net radiation heat transfer is from surface 2 to surface 1.
Now consider an enclosure consisting of N black surfaces maintained at
specified temperatures. The net radiation heat transfer from any surface i of
this enclosure is determined by adding up the net radiation heat transfers from
surface i to each of the surfaces of the enclosure:
N ·
Qi
j N ·
Qi → j
1 Ai Fi → j (Ti4
j Tj4) (W) (1220) 1 ·
Again a negative value for Q indicates that net radiation heat transfer is to
surface i (i.e., surface i gains radiation energy instead of losing). Also, the net
heat transfer from a surface to itself is zero, regardless of the shape of the
surface. EXAMPLE 12–6 Radiation Heat Transfer in a Black Furnace
2 T2 = 1500 K Consider the 5m 5m 5m cubical furnace shown in Figure 12–19, whose
surfaces closely approximate black surfaces. The base, top, and side surfaces
of the furnace are maintained at uniform temperatures of 800 K, 1500 K, and
500 K, respectively. Determine (a) the net rate of radiation heat transfer between the base and the side surfaces, (b) the net rate of radiation heat transfer
between the base and the top surface, and (c) the net radiation heat transfer
from the base surface. SOLUTION The surfaces of a cubical furnace are black and are maintained at
uniform temperatures. The net rate of radiation heat transfer between the base
and side surfaces, between the base and the top surface, from the base surface
are to be determined.
Assumptions The surfaces are black and isothermal. 3
T3 = 500 K 1
T1 = 800 K FIGURE 12–19
The cubical furnace of black surfaces
considered in Example 12–6. cen58933_ch12.qxd 9/9/2002 9:48 AM Page 622 622
HEAT TRANSFER Analysis (a) Considering that the geometry involves six surfaces, we may be
tempted at first to treat the furnace as a sixsurface enclosure. However, the
four side surfaces possess the same properties, and thus we can treat them as
a single side surface in radiation analysis. We consider the base surface to be
surface 1, the top surface to be surface 2, and the side surfaces to be surface
·
·
·
3. Then the problem reduces to determining Q 1 → 3, Q 1 → 2, and Q 1.
·
The net rate of radiation heat transfer Q 1 → 3 from surface 1 to surface 3 can
be determined from Eq. 12–19, since both surfaces involved are black, by replacing the subscript 2 by 3: ·
Q1 → 3 A1F1 → 3 (T14 T34) But first we need to evaluate the view factor F1 → 3. After checking the view factor charts and tables, we realize that we cannot determine this view factor directly. However, we can determine the view factor F1 → 2 directly from Figure
12–5 to be F1 → 2
0.2, and we know that F1 → 1
0 since surface 1 is a
plane. Then applying the summation rule to surface 1 yields F1 → 1 F1 → 2 F1 → 3 1 or F1 → 3 1 F1 → 1 F1 → 2 1 0 0.2 0.8 Substituting, ·
Q1 → 3 (25 m2)(0.8)(5.67 10 8 W/m2 · K4)[(800 K)4
394 103 W 394 kW (500 K)4] ·
(b) The net rate of radiation heat transfer Q 1 → 2 from surface 1 to surface 2 is
determined in a similar manner from Eq. 12–19 to be ·
Q1 → 2 A1F1 → 2 (T14 T24)
(25 m2)(0.2)(5.67 10 8 W/m2 · K4)[(800 K)4
1319 kW
1319 103 W (1500 K)4] The negative sign indicates that net radiation heat transfer is from surface 2 to
surface 1.
·
(c) The net radiation heat transfer from the base surface Q 1 is determined from
Eq. 12–20 by replacing the subscript i by 1 and taking N 3:
3 ·
Q1 ·
Q1 → j ·
Q1 → 1 j ( 1319 kW)
925 kW ·
Q1 → 3 1 0 ·
Q1 → 2
(394 kW) Again the negative sign indicates that net radiation heat transfer is to surface 1.
That is, the base of the furnace is gaining net radiation at a rate of about
925 kW. cen58933_ch12.qxd 9/9/2002 9:48 AM Page 623 623
CHAPTER 12 12–4 I RADIATION HEAT TRANSFER:
DIFFUSE, GRAY SURFACES The analysis of radiation transfer in enclosures consisting of black surfaces is
relatively easy, as we have seen above, but most enclosures encountered in
practice involve nonblack surfaces, which allow multiple reflections to occur.
Radiation analysis of such enclosures becomes very complicated unless some
simplifying assumptions are made.
To make a simple radiation analysis possible, it is common to assume the
surfaces of an enclosure to be opaque, diffuse, and gray. That is, the surfaces
are nontransparent, they are diffuse emitters and diffuse reflectors, and their
radiation properties are independent of wavelength. Also, each surface of the
enclosure is isothermal, and both the incoming and outgoing radiation are uniform over each surface. But first we review the concept of radiosity discussed
in Chap. 11. Radiosity
Surfaces emit radiation as well as reflect it, and thus the radiation leaving a
surface consists of emitted and reflected parts. The calculation of radiation
heat transfer between surfaces involves the total radiation energy streaming
away from a surface, with no regard for its origin. The total radiation energy
leaving a surface per unit time and per unit area is the radiosity and is
denoted by J (Fig. 12–20).
1), the
For a surface i that is gray and opaque ( i
i and
i
i
radiosity can be expressed as
Ji Radiation emitted
by surface i
Ebi
i
iGi
(1
iEbi
i)Gi Ebi Ti4 (blackbody) Reflected Emitted
radiation radiation
ε Eb G (1221) where Ebi
Ti4 is the blackbody emissive power of surface i and Gi is
irradiation (i.e., the radiation energy incident on surface i per unit time per
unit area).
For a surface that can be approximated as a blackbody ( i 1), the radiosity relation reduces to
Ji Incident
radiation ρG Radiation reflected
by surface i
(W/m2) Radiosity, J (1222) That is, the radiosity of a blackbody is equal to its emissive power. This is
expected, since a blackbody does not reflect any radiation, and thus radiation
coming from a blackbody is due to emission only. Net Radiation Heat Transfer to or from a Surface
During a radiation interaction, a surface loses energy by emitting radiation and
gains energy by absorbing radiation emitted by other surfaces. A surface experiences a net gain or a net loss of energy, depending on which quantity is
larger. The net rate of radiation heat transfer from a surface i of surface area Ai
·
is denoted by Q i and is expressed as Surface FIGURE 12–20
Radiosity represents the sum of the
radiation energy emitted and
reflected by a surface. cen58933_ch12.qxd 9/9/2002 9:48 AM Page 624 624
HEAT TRANSFER ·
Qi Radiation leaving
entire surface i
Ai(Ji Gi) Radiation incident
on entire surface i (W) (1223) Solving for Gi from Eq. 12–21 and substituting into Eq. 12–23 yields
·
Qi Ai Ji Ji Ai i Ebi 1 1 i i
i (Ebi Ji) (W) (1224) In an electrical analogy to Ohm’s law, this equation can be rearranged as
·
Qi Ebi Ji
Ri (W) (1225) where
Ri . Qi
Ebi
Surface
i 1 – εi
Ri = ——–
Ai εi Ji FIGURE 12–21
Electrical analogy of surface
resistance to radiation. 1 i Ai (1226) i is the surface resistance to radiation. The quantity Ebi Ji corresponds to a
potential difference and the net rate of radiation heat transfer corresponds to
current in the electrical analogy, as illustrated in Figure 12–21.
The direction of the net radiation heat transfer depends on the relative magnitudes of Ji (the radiosity) and Ebi (the emissive power of a blackbody at the
temperature of the surface). It will be from the surface if Ebi Ji and to the
·
surface if Ji Ebi. A negative value for Q i indicates that heat transfer is to
the surface. All of this radiation energy gained must be removed from the
other side of the surface through some mechanism if the surface temperature
is to remain constant.
The surface resistance to radiation for a blackbody is zero since i 1 and
Ebi. The net rate of radiation heat transfer in this case is determined
Ji
directly from Eq. 12–23.
Some surfaces encountered in numerous practical heat transfer applications
are modeled as being adiabatic since their back sides are well insulated and
the net heat transfer through them is zero. When the convection effects on the
front (heat transfer) side of such a surface is negligible and steadystate conditions are reached, the surface must lose as much radiation energy as it gains,
·
and thus Q i 0. In such cases, the surface is said to reradiate all the radiation
energy it receives, and such a surface is called a reradiating surface. Setting
·
Q i 0 in Eq. 12–25 yields
Ji Ebi Ti4 (W/m2) (1227) Therefore, the temperature of a reradiating surface under steady conditions
can easily be determined from the equation above once its radiosity is known.
Note that the temperature of a reradiating surface is independent of its emissivity. In radiation analysis, the surface resistance of a reradiating surface is
disregarded since there is no net heat transfer through it. (This is like the fact
that there is no need to consider a resistance in an electrical network if no current is flowing through it.) cen58933_ch12.qxd 9/9/2002 9:48 AM Page 625 625
CHAPTER 12 Net Radiation Heat Transfer
between Any Two Surfaces Ebj Consider two diffuse, gray, and opaque surfaces of arbitrary shape maintained
at uniform temperatures, as shown in Figure 12–22. Recognizing that the radiosity J represents the rate of radiation leaving a surface per unit surface area
and that the view factor Fi → j represents the fraction of radiation leaving surface i that strikes surface j, the net rate of radiation heat transfer from surface
i to surface j can be expressed as
Radiation leaving
the entire surface i
that strikes surface j ·
Qi → j Ai Ji Fi → j Radiation leaving
the entire surface j
that strikes surface i Aj Jj Fj → i ·
Qi → j Rj Ai Fi → j (Ji Jj . Qij 1
Rij = ——
Ai Fij
Ji
Ri (1228)
Ebi (W) Applying the reciprocity relation Ai Fi → j Surface i FIGURE 12–22
Electrical analogy of
space resistance to radiation. Aj Fj → i yields
Jj) Surface j (W) (1229) Again in analogy to Ohm’s law, this equation can be rearranged as
·
Qi → j Ji Jj
Ri → j Ri → j 1
Ai Fi → j (W) (1230) where
(1231) N ·
Qi
j N ·
Qi → j N Ai Fi → j (Ji 1 j Jj) 1 j Ji Jj
Ri → j
1 (W) (1232) Ri j Ji Jj
Ri → j
1 (W) Ri (1233) i1 J Ebi Ji J2 R i2
R i(N – R iN N Ji Qi R . The network representation of net radiation heat transfer from surface i to the
remaining surfaces of an Nsurface enclosure is given in Figure 12–23. Note
·
that Q i → i (the net rate of heat transfer from a surface to itself) is zero regardless of the shape of the surface. Combining Eqs. 12–25 and 12–32 gives
Ebi 1 is the space resistance to radiation. Again the quantity Ji Jj corresponds to
a potential difference, and the net rate of heat transfer between two surfaces
corresponds to current in the electrical analogy, as illustrated in Figure 12–22.
The direction of the net radiation heat transfer between two surfaces de·
pends on the relative magnitudes of Ji and Jj. A positive value for Q i → j indicates that net heat transfer is from surface i to surface j. A negative value
indicates the opposite.
In an Nsurface enclosure, the conservation of energy principle requires that
the net heat transfer from surface i be equal to the sum of the net heat transfers
from surface i to each of the N surfaces of the enclosure. That is, 1) JN Surface i –1 JN FIGURE 12–23
Network representation of net
radiation heat transfer from surface i
to the remaining surfaces of an
Nsurface enclosure. cen58933_ch12.qxd 9/9/2002 9:48 AM Page 626 626
HEAT TRANSFER which has the electrical analogy interpretation that the net radiation flow from
a surface through its surface resistance is equal to the sum of the radiation
flows from that surface to all other surfaces through the corresponding space
resistances. Methods of Solving Radiation Problems
In the radiation analysis of an enclosure, either the temperature or the net rate
of heat transfer must be given for each of the surfaces to obtain a unique solution for the unknown surface temperatures and heat transfer rates. There are
two methods commonly used to solve radiation problems. In the first method,
Eqs. 12–32 (for surfaces with specified heat transfer rates) and 12–33 (for surfaces with specified temperatures) are simplified and rearranged as
Surfaces with specified
·
net heat transfer rate Q i
Surfaces with specified
temperature Ti ·
Qi N Ai Fi → j(Ji
j Ti4 Ji Jj) (1234) 1
N 1 i
i Fi → j(Ji
j Jj) (1235) 1 ·
Note that Q i
0 for insulated (or reradiating) surfaces, and Ti4
Ji for
black surfaces since i 1 in that case. Also, the term corresponding to j i
will drop out from either relation since Ji Jj Ji Ji 0 in that case.
The equations above give N linear algebraic equations for the determination
of the N unknown radiosities for an Nsurface enclosure. Once the radiosities
J1, J2, . . . , JN are available, the unknown heat transfer rates can be determined
from Eq. 12–34 while the unknown surface temperatures can be determined
from Eq. 12–35. The temperatures of insulated or reradiating surfaces can be
·
determined from Ti4 Ji. A positive value for Q i indicates net radiation heat
transfer from surface i to other surfaces in the enclosure while a negative value
indicates net radiation heat transfer to the surface.
The systematic approach described above for solving radiation heat transfer
problems is very suitable for use with today’s popular equation solvers such
as EES, Mathcad, and Matlab, especially when there are a large number of
surfaces, and is known as the direct method (formerly, the matrix method,
since it resulted in matrices and the solution required a knowledge of linear
algebra). The second method described below, called the network method, is
based on the electrical network analogy.
The network method was first introduced by A. K. Oppenheim in the 1950s
and found widespread acceptance because of its simplicity and emphasis on
the physics of the problem. The application of the method is straightforward:
draw a surface resistance associated with each surface of an enclosure and
connect them with space resistances. Then solve the radiation problem by
treating it as an electrical network problem where the radiation heat transfer
replaces the current and radiosity replaces the potential.
The network method is not practical for enclosures with more than three or
four surfaces, however, because of the increased complexity of the network.
Next we apply the method to solve radiation problems in two and threesurface enclosures. cen58933_ch12.qxd 9/9/2002 9:48 AM Page 627 627
CHAPTER 12 Radiation Heat Transfer in TwoSurface Enclosures
Consider an enclosure consisting of two opaque surfaces at specified temperatures T1 and T2, as shown in Fig. 12–24, and try to determine the net rate of
radiation heat transfer between the two surfaces with the network method.
Surfaces 1 and 2 have emissivities 1 and 2 and surface areas A1 and A2 and
are maintained at uniform temperatures T1 and T2, respectively. There are only
two surfaces in the enclosure, and thus we can write
·
Q 12 ·
Q1 ·
Q2 Eb1
R1 Eb2
R12 . ·
Q1 R2 ε2
A2
T2
2 1 Eb1 That is, the net rate of radiation heat transfer from surface 1 to surface 2 must
equal the net rate of radiation heat transfer from surface 1 and the net rate of
radiation heat transfer to surface 2.
The radiation network of this twosurface enclosure consists of two surface
resistances and one space resistance, as shown in Figure 12–24. In an electrical network, the electric current flowing through these resistances connected
in series would be determined by dividing the potential difference between
points A and B by the total resistance between the same two points. The net
rate of radiation transfer is determined in the same manner and is expressed as
·
Q 12 . Q12 ε1
A1
T1 . Q1 J1 1 – ε1
R1 = ——–
A1ε1 Q12 1
R12 = ——–
A1F12 . J2 Q2 Eb2 1 – ε2
R2 = ——–
A2ε2 FIGURE 12–24
Schematic of a twosurface
enclosure and the radiation
network associated with it. ·
Q2 or
·
Q 12 (T14
1
A1 1
1 T24) 1
A1 F12 1
A2 (W) (1236) 2
2 This important result is applicable to any two gray, diffuse, opaque surfaces
that form an enclosure. The view factor F12 depends on the geometry
and must be determined first. Simplified forms of Eq. 12–36 for some familiar arrangements that form a twosurface enclosure are given in Table 12–3.
Note that F12 1 for all of these special cases. EXAMPLE 12–7 Radiation Heat Transfer between Parallel Plates Two very large parallel plates are maintained at uniform temperatures T1
800 K and T2
500 K and have emissivities 1
0.2 and 2
0.7, respectively, as shown in Figure 12–25. Determine the net rate of radiation heat transfer between the two surfaces per unit surface area of the plates. SOLUTION Two large parallel plates are maintained at uniform temperatures.
The net rate of radiation heat transfer between the plates is to be determined.
Assumptions Both surfaces are opaque, diffuse, and gray.
Analysis The net rate of radiation heat transfer between the two plates per unit
area is readily determined from Eq. 12–38 to be 1 ε1 = 0.2 . T1 = 800 K Q12
2 ε 2 = 0.7
T2 = 500 K FIGURE 12–25
The two parallel plates
considered in Example 12–7. cen58933_ch12.qxd 9/9/2002 9:49 AM Page 628 628
HEAT TRANSFER TABLE 12–3
Small object in a large cavity
A
—1 ≈ 0
–
A2 A1, T1, ε1 . 4
Q12 = A1σε1(T 4 – T 2 )
1 (1237) F12 = 1
A2, T2, ε2 Infinitely large parallel plates
A1, T1, ε1 A2, T2, ε 2 4
.
A σ (T 4 – T 2 )
1
Q12 = ———————
1
1
—+—–1
ε
ε (1238) 4
.
A1σ (T 4 – T 2 )
1
Q12 = —————————
r
1 + 1 – ε2 —–
— ––— 1
ε1
ε2
r2 (1239) 4
.
A1σ (T 4 – T 2 )
1
Q12 = —————————
1 – ε2 r1 2
1
— + ––— —–
ε1
ε2
r2 A1 = A2 = A
F12 = 1 (1240) 1 2 Infinitely long concentric cylinders
r1 r2
A1
r1
—– = —–
A2
r2
F12 = 1 Concentric spheres r1
r2 A1
r1 2
—– = —–
A2
r2
F12 = 1 ·
q 12 ·
Q 12
A (T14 T24) 1 1 1 2 1 (5.67 10 8 W/m2 · K4)[(800 K)4
1
1
1
0.2 0.7 (500 K)4] 3625 W/m2
Discussion Note that heat at a net rate of 3625 W is transferred from plate 1
to plate 2 by radiation per unit surface area of either plate. cen58933_ch12.qxd 9/9/2002 9:49 AM Page 629 629
CHAPTER 12 Radiation Heat Transfer
in ThreeSurface Enclosures
We now consider an enclosure consisting of three opaque, diffuse, gray surfaces, as shown in Figure 12–26. Surfaces 1, 2, and 3 have surface areas
A1, A2, and A3; emissivities 1, 2, and 3; and uniform temperatures T1, T2, and
T3, respectively. The radiation network of this geometry is constructed by following the standard procedure: draw a surface resistance associated with each
of the three surfaces and connect these surface resistances with space resistances, as shown in the figure. Relations for the surface and space resistances
are given by Eqs. 12–26 and 12–31. The three endpoint potentials Eb1, Eb2,
and Eb3 are considered known, since the surface temperatures are specified.
Then all we need to find are the radiosities J1, J2, and J3. The three equations
for the determination of these three unknowns are obtained from the requirement that the algebraic sum of the currents (net radiation heat transfer) at
each node must equal zero. That is,
J3 Eb1 J1 J2 J1
R1
R12
J1 J2 Eb2 J2
R12
R2
J1 J3
R13 J2 J1
R13 J3 J2
R23 Eb3 J3
R3 J3
R23 0
0
0 (1241) Once the radiosities J1, J2, and J3 are available, the net rate of radiation heat
transfers at each surface can be determined from Eq. 12–32.
The set of equations above simplify further if one or more surfaces are “speTi4 for a black or reradiating surcial” in some way. For example, Ji Ebi
·
0 for a reradiating surface. Finally, when the net rate of
face. Also, Q i
·
radiation heat transfer Q i is specified at surface i instead of the temperature,
·
the term (Ebi Ji)/Ri should be replaced by the specified Q i. ε1, A1, T1
ε 2, A2, T2 1
2 .
Q1 Eb1 J1
1 – ε1
R1 = ——–
A1ε1 1
R12 = ——–
A1F12 . Q12 1
R13 = ——–
A1F13
3 . Q23 . Q13 Eb2 J2
1 – ε2
R2 = ——–
A2ε2 . Q2 1
R23 = ——–
A2 F23
J3 ε 3 , A3, T3 1 – ε3
R3 = ——–
A 3ε 3
Eb3 . Q3 FIGURE 12–26
Schematic of a threesurface enclosure and the radiation network associated with it. cen58933_ch12.qxd 9/9/2002 9:49 AM Page 630 630
HEAT TRANSFER
T1 = 700 K
ε1 = 0.8 1
ro 3
Black
T3 = 400 K H EXAMPLE 12–8 Radiation Heat Transfer in a Cylindrical Furnace Consider a cylindrical furnace with r0
H
1 m, as shown in Figure 12–27.
The top (surface 1) and the base (surface 2) of the furnace has emissivities
0.8 and 2
0.4, respectively, and are maintained at uniform tempera1
tures T1
700 K and T2
500 K. The side surface closely approximates a
blackbody and is maintained at a temperature of T3
400 K. Determine the
net rate of radiation heat transfer at each surface during steady operation and
explain how these surfaces can be maintained at specified temperatures. SOLUTION The surfaces of a cylindrical furnace are maintained at uniform
temperatures. The net rate of radiation heat transfer at each surface during
steady operation is to be determined.
2 T2 = 500 K
ε2 = 0.4 FIGURE 12–27
The cylindrical furnace
considered in Example 12–8. Assumptions 1 Steady operating conditions exist. 2 The surfaces are opaque,
diffuse, and gray. 3 Convection heat transfer is not considered.
Analysis We will solve this problem systematically using the direct method to
demonstrate its use. The cylindrical furnace can be considered to be a threesurface enclosure with surface areas of A1
A3 ro2 A2 2 roH (1 m)2 3.14 m2
2 (1 m)(1 m) 6.28 m2 The view factor from the base to the top surface is, from Figure 12–7, F12
0.38. Then the view factor from the base to the side surface is determined by
applying the summation rule to be F11 F12 F13 1 → F13 1 F11 F12 1 0 0.38 0.62 since the base surface is flat and thus F11 0. Noting that the top and bottom
surfaces are symmetric about the side surface, F21
F12
0.38 and F23
F13
0.62. The view factor F31 is determined from the reciprocity relation, A1F13 A3F31 → F31 F13(A1/A3) (0.62)(0.314/0.628) 0.31 Also, F32 F31 0.31 because of symmetry. Now that all the view factors are
available, we apply Eq. 12–35 to each surface to determine the radiosities:
Top surface (i T14 1): Bottom surface (i
Side surface (i 2):
3): J1 T24 J2 T34 J3 1 1 [F1 → 2 (J1 J2) F1 → 3 (J1 J3)] 2 [F2 → 1 (J2 J1) F2 → 3 (J2 J3)] 1 1
2 0 (since surface 3 is black and thus 3 1) Substituting the known quantities, (5.67 10 8 W/m2 · K4)(700 K)4 J1 (5.67 10 8 W/m2 · K4)(500 K)4 J2 (5.67 10 8 W/m2 · K4)(400 K)4 J3 1 0.8
[0.38(J1
0.8 J2) 0.68(J1 J3)] 1 0.4
[0.28(J2
0.4 J1) 0.68(J2 J3)] cen58933_ch12.qxd 9/9/2002 9:49 AM Page 631 631
CHAPTER 12 Solving the equations above for J1, J2, and J3 gives J1 11,418 W/m2, J2 4562 W/m2, and 1452 W/m2 J3 Then the net rates of radiation heat transfer at the three surfaces are determined from Eq. 12–34 to be ·
Q1 A1[F1 → 2 (J1 J2) F1 → 3 (J1 J3)]
(3.14 m2)[0.38(11,418 4562) 0.62(11,418 1452)] W/m2
27.6 103 W 27.6 kW
A2[F2 → 1 (J2 J1) F2 → 3 (J2 J3)]
(3.12 m2)[0.38(4562 11,418) 0.62(4562 1452)] W/m2
2.13 103 W
2.13 kW
A3[F3 → 1 (J3 J1) F3 → 2 (J3 J2)]
(6.28 m2)[0.31(1452 11,418) 0.31(1452 4562)] W/m2
25.5 103 W
25.5 kW ·
Q2 ·
Q3 Note that the direction of net radiation heat transfer is from the top surface to
the base and side surfaces, and the algebraic sum of these three quantities
must be equal to zero. That is, ·
Q1 ·
Q2 ·
Q3 27.6 ( 2.13) ( 25.5) 0 Discussion To maintain the surfaces at the specified temperatures, we must
supply heat to the top surface continuously at a rate of 27.6 kW while removing
2.13 kW from the base and 25.5 kW from the side surfaces.
The direct method presented here is straightforward, and it does not require
the evaluation of radiation resistances. Also, it can be applied to enclosures
with any number of surfaces in the same manner. EXAMPLE 12–9 Radiation Heat Transfer in a Triangular Furnace A furnace is shaped like a long equilateral triangular duct, as shown in Figure
12–28. The width of each side is 1 m. The base surface has an emissivity of
0.7 and is maintained at a uniform temperature of 600 K. The heated leftside
surface closely approximates a blackbody at 1000 K. The rightside surface is
well insulated. Determine the rate at which heat must be supplied to the heated
side externally per unit length of the duct in order to maintain these operating
conditions.
. Q1 Eb1 2
T2 = 1000 K
Black J1 R12 J2 = Eb2 R1 3 . . Q2 = – Q1 Insulated
R13
1 ε1 = 0.7
T1 = 600 K R23 (J3 = Eb3 ) . Q3 = 0 FIGURE 12–28
The triangular furnace
considered in Example 12–9. cen58933_ch12.qxd 9/9/2002 9:49 AM Page 632 632
HEAT TRANSFER SOLUTION Two of the surfaces of a long equilateral triangular furnace are
maintained at uniform temperatures while the third surface is insulated. The external rate of heat transfer to the heated side per unit length of the duct during
steady operation is to be determined.
Assumptions 1 Steady operating conditions exist. 2 The surfaces are opaque,
diffuse, and gray. 3 Convection heat transfer is not considered.
Analysis The furnace can be considered to be a threesurface enclosure with a
radiation network as shown in the figure, since the duct is very long and thus
the end effects are negligible. We observe that the view factor from any surface
to any other surface in the enclosure is 0.5 because of symmetry. Surface 3 is
a reradiating surface since the net rate of heat transfer at that surface is zero.
·
·
Then we must have Q 1
Q 2, since the entire heat lost by surface 1 must
be gained by surface 2. The radiation network in this case is a simple series–
·
parallel connection, and we can determine Q 1 directly from
Eb1 ·
Q1
R1 1
R12 Eb1 Eb2
1 1
R13 R23 1
A1 1
1 Eb2
1 1 A1 F12 1/A1 F13 1/A2 F23 where A1
F12
Eb1
Eb2 A2 A3 wL 1 m 1 m 1 m2
(per unit length of the duct)
F13 F23 0.5
(symmetry)
T14 (5.67 10 8 W/m2 · K4)(600 K)4 7348 W/m2
T24 (5.67 10 8 W/m2 · K4)(1000 K)4 56,700 W/m2 Substituting, ·
Q1 (56,700
1 0.7
0.7 1 m2
28.0 103 (0.5 1 m2) 7348) W/m2
1 1
1/(0.5 2 1m) 1/(0.5 2 1m) 28.0 kW Therefore, heat at a rate of 28 kW must be supplied to the heated surface per
unit length of the duct to maintain steady operation in the furnace.
Solar
energy
Glass cover
ε = 0.9
70°F
4 in.
2 in.
Aluminum tube
ε = 0.95
Water FIGURE 12–29
Schematic for Example 12–10. EXAMPLE 12–10 Heat Transfer through a Tubular Solar Collector A solar collector consists of a horizontal aluminum tube having an outer diameter of 2 in. enclosed in a concentric thin glass tube of 4in. diameter, as shown
in Figure 12–29. Water is heated as it flows through the tube, and the space
between the aluminum and the glass tubes is filled with air at 1 atm pressure.
The pump circulating the water fails during a clear day, and the water temperature in the tube starts rising. The aluminum tube absorbs solar radiation at a
rate of 30 Btu/h per foot length, and the temperature of the ambient air outside
is 70°F. The emissivities of the tube and the glass cover are 0.95 and 0.9,
respectively. Taking the effective sky temperature to be 50°F, determine the cen58933_ch12.qxd 9/9/2002 9:49 AM Page 633 633
CHAPTER 12 temperature of the aluminum tube when steady operating conditions are
established (i.e., when the rate of heat loss from the tube equals the amount of
solar energy gained by the tube). SOLUTION The circulating pump of a solar collector that consists of a horizontal tube and its glass cover fails. The equilibrium temperature of the tube is
to be determined.
Assumptions 1 Steady operating conditions exist. 2 The tube and its cover are
isothermal. 3 Air is an ideal gas. 4 The surfaces are opaque, diffuse, and gray
for infrared radiation. 5 The glass cover is transparent to solar radiation.
Properties The properties of air should be evaluated at the average temperature. But we do not know the exit temperature of the air in the duct, and thus
we cannot determine the bulk fluid and glass cover temperatures at this point,
and thus we cannot evaluate the average temperatures. Therefore, we will assume the glass temperature to be 110°F, and use properties at an anticipated
average temperature of (70 110)/2 90°F (Table A15E), k 0.01505 Btu/h ft °F
0.6310 ft2/h 1.753 Pr
10 4 ft2/s 0.7275
1
1
Tave 550 R Analysis This problem was solved in Chapter 9 by disregarding radiation heat
transfer. Now we will repeat the solution by considering natural convection and
radiation occurring simultaneously.
We have a horizontal cylindrical enclosure filled with air at 1 atm pressure.
The problem involves heat transfer from the aluminum tube to the glass cover
and from the outer surface of the glass cover to the surrounding ambient air.
When steady operation is reached, these two heat transfer rates must equal the
rate of heat gain. That is, ·
Q tubeglass ·
Q glassambient ·
Q solar gain 30 Btu/h (per foot of tube) The heat transfer surface area of the glass cover is Ao Aglass ( Do L) (4/12 ft)(1 ft) 1.047 ft2 (per foot of tube) To determine the Rayleigh number, we need to know the surface temperature of
the glass, which is not available. Therefore, it is clear that the solution will require a trialanderror approach. Assuming the glass cover temperature to be
110°F, the Rayleigh number, the Nusselt number, the convection heat transfer
coefficient, and the rate of natural convection heat transfer from the glass cover
to the ambient air are determined to be RaDo Nu T ) D3
o g (To
2 Pr (32.2 ft/s2)[1/(550 R)](110 70 R)(4/12 ft)3
(0.7275) 2.054 106
(1.753 10 4 ft2/s)2
2
0.387 Ra1/6
0.387(2.054 106)1/6
Do
0.6
0.6
9/16 8/27
[1 (0.559/Pr) ]
[1 (0.559/0.7275)9/16]8/27
17.89 2 cen58933_ch12.qxd 9/9/2002 9:49 AM Page 634 634
HEAT TRANSFER 0.01505 Btu/h · ft · °F
k
Nu
(17.89) 0.8075 Btu/h ft2 °F
Do
4/12 ft
ho Ao(To T ) (0.8075 Btu/h ft2 °F)(1.047 ft2)(110 70)°F
33.8 Btu/h ho
·
Q o, conv Also, ·
Q o, rad 4
Ao(To4 Tsky)
(0.9)(0.1714 10
61.2 Btu/h
o 8 Btu/h ft2 R4)(1.047 ft2)[(570 R)4 (510 R)4] Then the total rate of heat loss from the glass cover becomes ·
Q o, total ·
Q o, conv ·
Q o, rad 33.8 61.2 95.0 Btu/h which is much larger than 30 Btu/h. Therefore, the assumed temperature of
110°F for the glass cover is high. Repeating the calculations with lower temperatures (including the evaluation of properties), the glass cover temperature
corresponding to 30 Btu/h is determined to be 78°F (it would be 106°F if radiation were ignored).
The temperature of the aluminum tube is determined in a similar manner
using the natural convection and radiation relations for two horizontal concentric cylinders. The characteristic length in this case is the distance between the
two cylinders, which is Lc (Do Di)/2 (4 2)/2 1 in. 1/12 ft Also, Ai Atube ( Di L) (2 /12 ft)(1 ft) 0.5236 ft2 (per foot of tube) We start the calculations by assuming the tube temperature to be 122°F, and
thus an average temperature of (78 122)/2 100°F 640 R. Using properties at 100°F, To)L3
c g (Ti RaL 2 Pr (32.2 ft/s2)[1/(640 R)](122 78 R)(1/12 ft)3
(0.726)
(1.809 10 4 ft2/s)2 3.249 104 3.249 104)1/4 The effective thermal conductivity is Fcyc keff [ln(Do /Di)]4
(Di 3/5 Do 3/5)5
[ln(4/2)]4
0.1466
3
(1/12 ft) [(2/12 ft) 3/5 (4/12 ft) 3/5]5
1/4
Pr
0.386k
(FcycRaL)1/4
0.861 Pr
0.726
0.386(0.01529 Btu/h ft °F)
(0.1466
0.861 0.726
0.04032 Btu/h ft °F
L3
c cen58933_ch12.qxd 9/9/2002 9:49 AM Page 635 635
CHAPTER 12 Then the rate of heat transfer between the cylinders by convection becomes ·
Q i, conv 2 keff
(T
To)
ln(Do /Di) i
2 (0.04032 Btu/h · ft °F)
(122
ln(4/2) 78)°F 16.1 Btu/h Also, ·
Q i, rad Ai (Ti4
11
i o (0.1714 To4)
o Di
Do
10 8 Btu/h · ft2 · R4)(0.5236 ft2)[(582 R)4
1
0.95 1 (538 R)4] 0.9 2 in.
0.9
4 in. 25.1 Btu/h
Then the total rate of heat loss from the glass cover becomes ·
Q i, total ·
Q i, conv ·
Q i, rad 16.1 25.1 41.1 Btu/h which is larger than 30 Btu/h. Therefore, the assumed temperature of 122°F for
the tube is high. By trying other values, the tube temperature corresponding
to 30 Btu/h is determined to be 112°F (it would be 180°F if radiation were
ignored). Therefore, the tube will reach an equilibrium temperature of 112°F
when the pump fails.
Discussion It is clear from the results obtained that radiation should always be
considered in systems that are heated or cooled by natural convection, unless
the surfaces involved are polished and thus have very low emissivities. 12–5 I RADIATION SHIELDS
AND THE RADIATION EFFECT Radiation heat transfer between two surfaces can be reduced greatly by inserting a thin, highreflectivity (lowemissivity) sheet of material between the
two surfaces. Such highly reflective thin plates or shells are called radiation
shields. Multilayer radiation shields constructed of about 20 sheets per cm
thickness separated by evacuated space are commonly used in cryogenic and
space applications. Radiation shields are also used in temperature measurements of fluids to reduce the error caused by the radiation effect when the
temperature sensor is exposed to surfaces that are much hotter or colder than
the fluid itself. The role of the radiation shield is to reduce the rate of radiation
heat transfer by placing additional resistances in the path of radiation heat
flow. The lower the emissivity of the shield, the higher the resistance.
Radiation heat transfer between two large parallel plates of emissivities 1 and 2 maintained at uniform temperatures T1 and T2 is given by
Eq. 12–38: cen58933_ch12.qxd 9/9/2002 9:49 AM Page 636 636
HEAT TRANSFER
(1) Shield
T1
ε1 T3
ε3, 1 T3
ε3, 2 . 1 – ε1
——–
ε1 A1 T2
ε2 . Q12 FIGURE 12–30
The radiation shield placed between
two parallel plates and the radiation
network associated with it. (2) . Q12 1 – ε3,1
–——–
ε3,1 A3 1
——–
A1 F13 Q12 1 – ε3, 2
–——–
ε3, 2 A3 1 – ε2
–——–
ε2 A2 1
——–
A3 F32 Eb1 Eb2 A (T14 T24)
1
1
1 ·
Q 12, no shield 1 2 Now consider a radiation shield placed between these two plates, as shown in
Figure 12–30. Let the emissivities of the shield facing plates 1 and 2 be 3, 1
and 3, 2, respectively. Note that the emissivity of different surfaces of the
shield may be different. The radiation network of this geometry is constructed,
as usual, by drawing a surface resistance associated with each surface and
connecting these surface resistances with space resistances, as shown in the
figure. The resistances are connected in series, and thus the rate of radiation
heat transfer is
·
Q 12, one shield Eb1
1
A1 1
A3 1
A1 F12 1
1 3, 1
3, 1 Noting that F13 F23 1 and A1
Eq. 12–42 simplifies to A2 Eb2
1
A3 1 1 1 2 3, 2 A3 A (T14 ·
Q 12, one shield 3, 2 1
A2 1
A3 F32 (1242)
2
2 A for infinite parallel plates,
T24)
1
3, 1 1 1
3, 2 (1243) 1 where the terms in the second set of parentheses in the denominator represent
the additional resistance to radiation introduced by the shield. The appearance
of the equation above suggests that parallel plates involving multiple radiation
shields can be handled by adding a group of terms like those in the second set
of parentheses to the denominator for each radiation shield. Then the radiation
heat transfer through large parallel plates separated by N radiation shields
becomes
·
Q 12, N shields A (T14
1 1 1 2 1 1 1 3, 1 3, 2 T24)
1 ··· 1 1 N, 1 N, 2 1
(1244) cen58933_ch12.qxd 9/9/2002 9:49 AM Page 637 637
CHAPTER 12 If the emissivities of all surfaces are equal, Eq. 12–44 reduces to
A (T14 ·
Q 12, N shields
(N 1) T24)
1 1 1
1 N 1 ·
Q 12, no shield (1245) Therefore, when all emissivities are equal, 1 shield reduces the rate of radiation heat transfer to onehalf, 9 shields reduce it to onetenth, and 19 shields
reduce it to onetwentieth (or 5 percent) of what it was when there were no
shields.
The equilibrium temperature of the radiation shield T3 in Figure 12–30 can
·
·
be determined by expressing Eq. 12–43 for Q 13 or Q 23 (which involves T3)
·
·
·
·
after evaluating Q 12 from Eq. 12–43 and noting that Q 12 Q 13 Q 23 when
steady conditions are reached.
Radiation shields used to reduce the rate of radiation heat transfer between
concentric cylinders and spheres can be handled in a similar manner. In case
of one shield, Eq. 12–42 can be used by taking F13 F23 1 for both cases
and by replacing the A’s by the proper area relations. Radiation Effect on Temperature Measurements
A temperature measuring device indicates the temperature of its sensor, which
is supposed to be, but is not necessarily, the temperature of the medium that
the sensor is in. When a thermometer (or any other temperature measuring device such as a thermocouple) is placed in a medium, heat transfer takes place
between the sensor of the thermometer and the medium by convection until
the sensor reaches the temperature of the medium. But when the sensor is surrounded by surfaces that are at a different temperature than the fluid, radiation
exchange will take place between the sensor and the surrounding surfaces.
When the heat transfers by convection and radiation balance each other, the
sensor will indicate a temperature that falls between the fluid and surface temperatures. Below we develop a procedure to account for the radiation effect
and to determine the actual fluid temperature.
Consider a thermometer that is used to measure the temperature of a
fluid flowing through a large channel whose walls are at a lower temperature
than the fluid (Fig. 12–31). Equilibrium will be established and the reading of
the thermometer will stabilize when heat gain by convection, as measured
by the sensor, equals heat loss by radiation (or vice versa). That is, on a unitarea basis,
·
q conv, to sensor
h(Tf Tth) Tth th 4
(Tth
h 4
Tw ) . Tw qrad Tf ·
q rad, from sensor
4
4
Tw )
th (Tth . qconv (K) Tw FIGURE 12–31
A thermometer used to measure the
temperature of a fluid in a channel. or
Tf Tth (1246) cen58933_ch12.qxd 9/9/2002 9:49 AM Page 638 638
HEAT TRANSFER where
Tf
Tth
Tw
h actual temperature of the fluid, K
temperature value measured by the thermometer, K
temperature of the surrounding surfaces, K
convection heat transfer coefficient, W/m2 · K
emissivity of the sensor of the thermometer The last term in Eq. 12–46 is due to the radiation effect and represents the
radiation correction. Note that the radiation correction term is most significant when the convection heat transfer coefficient is small and the emissivity
of the surface of the sensor is large. Therefore, the sensor should be coated
with a material of high reflectivity (low emissivity) to reduce the radiation
effect.
Placing the sensor in a radiation shield without interfering with the fluid
flow also reduces the radiation effect. The sensors of temperature measurement devices used outdoors must be protected from direct sunlight since the
radiation effect in that case is sure to reach unacceptable levels.
The radiation effect is also a significant factor in human comfort in heating
and airconditioning applications. A person who feels fine in a room at a specified temperature may feel chilly in another room at the same temperature as
a result of the radiation effect if the walls of the second room are at a considerably lower temperature. For example, most people will feel comfortable in
a room at 22°C if the walls of the room are also roughly at that temperature.
When the wall temperature drops to 5°C for some reason, the interior temperature of the room must be raised to at least 27°C to maintain the same level
of comfort. Therefore, wellinsulated buildings conserve energy not only by
reducing the heat loss or heat gain, but also by allowing the thermostats to be
set at a lower temperature in winter and at a higher temperature in summer
without compromising the comfort level. EXAMPLE 12–11 1 3 2 ε1 = 0.2
T1 = 800 K
ε3 = 0.1 ε2 = 0.7
T2 = 500 K . q12 A thin aluminum sheet with an emissivity of 0.1 on both sides is placed between two very large parallel plates that are maintained at uniform temperatures
T1 800 K and T2 500 K and have emissivities 1 0.2 and 2 0.7, respectively, as shown in Fig. 12–32. Determine the net rate of radiation heat
transfer between the two plates per unit surface area of the plates and compare
the result to that without the shield. SOLUTION A thin aluminum sheet is placed between two large parallel plates
maintained at uniform temperatures. The net rates of radiation heat transfer between the two plates with and without the radiation shield are to be determined.
Assumptions FIGURE 12–32
Schematic for Example 12–11. Radiation Shields The surfaces are opaque, diffuse, and gray. Analysis The net rate of radiation heat transfer between these two plates without the shield was determined in Example 12–7 to be 3625 W/m2. Heat transfer in the presence of one shield is determined from Eq. 12–43 to be cen58933_ch12.qxd 9/9/2002 9:49 AM Page 639 639
CHAPTER 12 ·
q 12, one shield ·
Q 12, one shield
A (T14 10 1
0.2
806 W/m2 8 1 1 (5.67 1 2 1 T24)
1 1 3, 1
4 3, 2 W/m2 · K4)[(800 K) 1
0.7 1 1
0.1 1
0.1 1 (500 K)4]
1 Discussion Note that the rate of radiation heat transfer reduces to about onefourth of what it was as a result of placing a radiation shield between the two
parallel plates. EXAMPLE 12–12 Radiation Effect on Temperature Measurements A thermocouple used to measure the temperature of hot air flowing in a duct
whose walls are maintained at Tw
400 K shows a temperature reading of
Tth
650 K (Fig. 12–33). Assuming the emissivity of the thermocouple
junction to be
0.6 and the convection heat transfer coefficient to be h
80 W/m2 · °C, determine the actual temperature of the air. SOLUTION The temperature of air in a duct is measured. The radiation effect
on the temperature measurement is to be quantified, and the actual air
temperature is to be determined.
Assumptions The surfaces are opaque, diffuse, and gray.
Analysis The walls of the duct are at a considerably lower temperature than
the air in it, and thus we expect the thermocouple to show a reading lower than
the actual air temperature as a result of the radiation effect. The actual air temperature is determined from Eq. 12–46 to be
Tf Tth th (650 K) 4
(Tth
h 4
Tw ) 0.6 (5.67 10 8 W/m2 · K4)[(650 K)4
80 W/m2 · °C (400 K)4] 715 K
Note that the radiation effect causes a difference of 65°C (or 65 K since °C
for temperature differences) in temperature reading in this case. 12–6 I K RADIATION EXCHANGE WITH
EMITTING AND ABSORBING GASES So far we considered radiation heat transfer between surfaces separated by a
medium that does not emit, absorb, or scatter radiation—a nonparticipating
medium that is completely transparent to thermal radiation. A vacuum satisfies this condition perfectly, and air at ordinary temperatures and pressures Tth = 650 K Tf ε = 0.6
Tw = 400 K FIGURE 12–33
Schematic for Example 12–12. cen58933_ch12.qxd 9/9/2002 9:49 AM Page 640 640
HEAT TRANSFER comes very close. Gases that consist of monatomic molecules such as Ar and
He and symmetric diatomic molecules such as N2 and O2 are essentially transparent to radiation, except at extremely high temperatures at which ionization
occurs. Therefore, atmospheric air can be considered to be a nonparticipating
medium in radiation calculations.
Gases with asymmetric molecules such as H2O, CO2, CO, SO2, and hydrocarbons HnCm may participate in the radiation process by absorption at moderate temperatures, and by absorption and emission at high temperatures such
as those encountered in combustion chambers. Therefore, air or any other
medium that contains such gases with asymmetric molecules at sufficient concentrations must be treated as a participating medium in radiation calculations. Combustion gases in a furnace or a combustion chamber, for example,
contain sufficient amounts of H2O and CO2, and thus the emission and absorption of gases in furnaces must be taken into consideration.
The presence of a participating medium complicates the radiation analysis
considerably for several reasons:
• A participating medium emits and absorbs radiation throughout its entire
volume. That is, gaseous radiation is a volumetric phenomena, and thus it
depends on the size and shape of the body. This is the case even if the
temperature is uniform throughout the medium.
• Gases emit and absorb radiation at a number of narrow wavelength bands.
This is in contrast to solids, which emit and absorb radiation over the
entire spectrum. Therefore, the gray assumption may not always be
appropriate for a gas even when the surrounding surfaces are gray.
• The emission and absorption characteristics of the constituents of a gas
mixture also depends on the temperature, pressure, and composition of
the gas mixture. Therefore, the presence of other participating gases
affects the radiation characteristics of a particular gas.
The propagation of radiation through a medium can be complicated further
by presence of aerosols such as dust, ice particles, liquid droplets, and soot
(unburned carbon) particles that scatter radiation. Scattering refers to the
change of direction of radiation due to reflection, refraction, and diffraction.
Scattering caused by gas molecules themselves is known as the Rayleigh scattering, and it has negligible effect on heat transfer. Radiation transfer in scattering media is considered in advanced books such as the ones by Modest
(1993, Ref. 12) and Siegel and Howell (1992, Ref. 14).
The participating medium can also be semitransparent liquids or solids such
as water, glass, and plastics. To keep complexities to a manageable level, we
will limit our consideration to gases that emit and absorb radiation. In particular, we will consider the emission and absorption of radiation by H2O and
CO2 only since they are the participating gases most commonly encountered
in practice (combustion products in furnaces and combustion chambers burning hydrocarbon fuels contain both gases at high concentrations), and they are
sufficient to demonstrate the basic principles involved. Radiation Properties of a Participating Medium
Consider a participating medium of thickness L. A spectral radiation beam of
intensity I , 0 is incident on the medium, which is attenuated as it propagates cen58933_ch12.qxd 9/9/2002 9:49 AM Page 641 641
CHAPTER 12 due to absorption. The decrease in the intensity of radiation as it passes
through a layer of thickness dx is proportional to the intensity itself and the
thickness dx. This is known as Beer’s law, and is expressed as (Fig. 12–34)
Iλ,0 dI (x) I (x)dx where the constant of proportionality
is the spectral absorption coefficient of the medium whose unit is m 1 (from the requirement of dimensional
homogeneity). This is just like the amount of interest earned by a bank
account during a time interval being proportional to the amount of money in
the account and the time interval, with the interest rate being the constant of
proportionality.
Separating the variables and integrating from x 0 to x L gives
I
I ,L L e (1248) ,0 where we have assumed the absorptivity of the medium to be independent
of x. Note that radiation intensity decays exponentially in accordance with
Beer ’s law.
The spectral transmissivity of a medium can be defined as the ratio of the
intensity of radiation leaving the medium to that entering the medium. That is,
I
I ,L L e (1249) ,0 Note that
1 when no radiation is absorbed and thus radiation intensity remains constant. Also, the spectral transmissivity of a medium represents the
fraction of radiation transmitted by the medium at a given wavelength.
Radiation passing through a nonscattering (and thus nonreflecting) medium
1, and the spectral abis either absorbed or transmitted. Therefore
sorptivity of a medium of thickness L is
1 1 L e (1250) From Kirchoff ’s law, the spectral emissivity of the medium is
1 e L IIλ(x)
λ(x) Iλ,L (1247) (1251) Note that the spectral absorptivity, transmissivity, and emissivity of a medium
are dimensionless quantities, with values less than or equal to 1. The spectral
absorption coefficient of a medium (and thus , , and ), in general, vary
with wavelength, temperature, pressure, and composition.
For an optically thick medium (a medium with a large value of L), Eq.
1. For L 5, for example,
0.993. There12–51 gives
fore, an optically thick medium emits like a blackbody at the given wavelength. As a result, an optically thick absorbingemitting medium with no
significant scattering at a given temperature Tg can be viewed as a “black surface” at Tg since it will absorb essentially all the radiation passing through it,
and it will emit the maximum possible radiation that can be emitted by a surface at Tg, which is Eb (Tg). 0 x
L
dx FIGURE 12–34
The attenuation of a radiation
beam while passing through an
absorbing medium of thickness L. cen58933_ch12.qxd 9/9/2002 9:49 AM Page 642 642
HEAT TRANSFER Emissivity and Absorptivity
of Gases and Gas Mixtures
The spectral absorptivity of CO2 is given in Figure 12–35 as a function of
wavelength. The various peaks and dips in the figure together with discontinuities show clearly the band nature of absorption and the strong nongray
characteristics. The shape and the width of these absorption bands vary with
temperature and pressure, but the magnitude of absorptivity also varies with
the thickness of the gas layer. Therefore, absorptivity values without specified
thickness and pressure are meaningless.
The nongray nature of properties should be considered in radiation calculations for high accuracy. This can be done using a band model, and thus performing calculations for each absorption band. However, satisfactory results
can be obtained by assuming the gas to be gray, and using an effective total
absorptivity and emissivity determined by some averaging process. Charts for
the total emissivities of gases are first presented by Hottel (Ref. 6), and they
have been widely used in radiation calculations with reasonable accuracy.
Alternative emissivity charts and calculation procedures have been developed
more recently by Edwards and Matavosian (Ref. 2). Here we present the
Hottel approach because of its simplicity.
Even with gray assumption, the total emissivity and absorptivity of a gas
depends on the geometry of the gas body as well as the temperature, pressure,
and composition. Gases that participate in radiation exchange such as CO2 and
H2O typically coexist with nonparticipating gases such as N2 and O2, and thus
radiation properties of an absorbing and emitting gas are usually reported for
a mixture of the gas with nonparticipating gases rather than the pure gas. The
emissivity and absorptivity of a gas component in a mixture depends primarily on its density, which is a function of temperature and partial pressure
of the gas.
The emissivity of H2O vapor in a mixture of nonparticipating gases is
plotted in Figure 12–36a for a total pressure of P 1 atm as a function of gas
temperature Tg for a range of values for Pw L, where Pw is the partial pressure
of water vapor and L is the mean distance traveled by the radiation beam.
Band designation λ, µm
15 4.3 1.0 2.7
10.4 Absorptivity α λ 0.8 FIGURE 12–35
Spectral absorptivity of
CO2 at 830 K and 10 atm
for a path length of 38.8 cm
(from Siegel and Howell, 1992). 9.4 0.6
4.8
2.0 0.4 0.2
0
20 10 8 6 5 4
3
Wavelength λ, µm 2.5 2 1.67 cen58933_ch12.qxd 9/9/2002 9:49 AM Page 643 643
CHAPTER 12
0.8 P 0.6 0.3 1 atm Pw L 20 ft • 0.4 0.2 0.1
0.08
0.06 1
0.6
0.4 0.04
0.03 0.2 0.06 0.01 0.02 0.1 0.04
0.06
0.04 0.03 0.006
0.004
0.003 0.02
0.015
0.01
0.007 0.01
0.008 0.006
0.005
0.004
0.003 0.01
0.008 0.02 0.006
300 0.02 Emissivity, εc Emissivity, εw 0.1
0.08 4.0 ft • atm
2.0
1.0
0.8
0.4
0.2
0.1
0.06
0.04 atm 10
5
3
2 0.3 Pc L 0.2 0.002
0.001 0.002 0.005
600 900 1200 1500 1800 2100 0.001
300 600 900 Gas temperature, Tg (K) 1200 1500 1800 2100 Gas temperature, Tg (K) (a) H20 (b) C02 FIGURE 12–36
Emissivities of H2O and CO2 gases in a mixture of nonparticipating gases at a total pressure of 1 atm
for a mean beam length of L (1 m atm 3.28 ft atm) (from Hottel, 1954, Ref. 6).
Cw 1.8 5 ft 1.6
1.4 0 PwL 0
0.0 1.2 • atm 0.25
0.50
1.00
2.50
5.00
10.0 Cc 2.0 1.0 1.5 0.8 1.0
0.8 PcL 0.6
0.5
0.4 1.0
0.5
0.25
0.12
0.05
0–0.02 0.6
0.4
0.2
0.0
0.0 0.2 0.4 0.6
(Pw 0.8 1.0 1.2 • tm
2.5 ft a 0.3
0.05 0.08 0.1 P)/2 (atm) (a) H20 0.2 0.3 0.5 0.8 1.0 2.0 3.0 50 Total pressure, P (atm)
(b) C02 FIGURE 12–37
Correction factors for the emissivities of H2O and CO2 gases at pressures other than 1 atm for use in the relations
Cw w, 1 atm and c Cc c, 1 atm (1 m atm 3.28 ft atm) (from Hottel, 1954, Ref. 6).
w Emissivity at a total pressure P other than P 1 atm is determined by multiplying the emissivity value at 1 atm by a pressure correction factor Cw obtained from Figure 12–37a for water vapor. That is, cen58933_ch12.qxd 9/9/2002 9:49 AM Page 644 644
HEAT TRANSFER Cw w (1252) w, 1 atm Note that Cw 1 for P 1 atm and thus (Pw P)/2 0.5 (a very low concentration of water vapor is used in the preparation of the emissivity chart in
Fig. 12–36a and thus Pw is very low). Emissivity values are presented in a
similar manner for a mixture of CO2 and nonparticipating gases in Fig.
12–36b and 12–37b.
Now the question that comes to mind is what will happen if the CO2 and
H2O gases exist together in a mixture with nonparticipating gases. The emissivity of each participating gas can still be determined as explained above using its partial pressure, but the effective emissivity of the mixture cannot be
determined by simply adding the emissivities of individual gases (although
this would be the case if different gases emitted at different wavelengths).
Instead, it should be determined from
g c w Cc c, 1 atm Cw (1253) w, 1 atm where
is the emissivity correction factor, which accounts for the overlap
of emission bands. For a gas mixture that contains both CO2 and H2O gases,
is plotted in Figure 12–38.
The emissivity of a gas also depends on the mean length an emitted radiation beam travels in the gas before reaching a bounding surface, and thus
the shape and the size of the gas body involved. During their experiments in
the 1930s, Hottel and his coworkers considered the emission of radiation from
a hemispherical gas body to a small surface element located at the center of
the base of the hemisphere. Therefore, the given charts represent emissivity
data for the emission of radiation from a hemispherical gas body of radius L
toward the center of the base of the hemisphere. It is certainly desirable to
extend the reported emissivity data to gas bodies of other geometries, and this
0.07 0.07
T 400 K Pc L Pw L T 800 K T 0.06 Pc L 0.05 Pc L Pw L 3.0 0.03 1.5
1.0
0.75
0.5
0.3
0.2
0.6
0.8 0.01
0
0 0.2 0.4 1.0 0 0.2 0.5
0.3
0.2
0.4
0.6 Pw
Pc 5 ft • atm 1.5
1.0
0.75 Pc 0.06
0.05
0.04
∆ε
0.03 0.75 2.0 0.02 0.5 0.01 0.8 1.0 0 0.2 0.3
0.2
0.4
0.6 Pw
Pw 5 ft • atm
3.0
2.0
1.5
1.0 3.0 2.0
0.02 Pw L 5 ft • atm 0.04
∆ε 1200 K and above 0.8 0
1.0 Pw
Pw Pc Pw FIGURE 12–38
Emissivity correction
for use in g
when both CO2 and H2O vapor are present in a gas mixture
w
c
(1 m atm 328 ft atm) (from Hottel, 1954, Ref. 6). cen58933_ch12.qxd 9/9/2002 9:49 AM Page 645 645
CHAPTER 12 is done by introducing the concept of mean beam length L, which represents
the radius of an equivalent hemisphere. The mean beam lengths for various
gas geometries are listed in Table 12–4. More extensive lists are available in
the literature [such as Hottel (1954, Ref. 6), and Siegel and Howell, (1992,
Ref. 14)]. The emissivities associated with these geometries can be determined from Figures 12–36 through 12–38 by using the appropriate mean
beam length.
Following a procedure recommended by Hottel, the absorptivity of a gas
that contains CO2 and H2O gases for radiation emitted by a source at temperature Ts can be determined similarly from
g c (1254) w where
and is determined from Figure 12–38 at the source temperature Ts. The absorptivities of CO2 and H2O can be determined from the emissivity charts (Figs. 12–36 and 12–37) as
CO2: c Cc (Tg / Ts)0.65 c(Ts, Pc LTs / Tg) (1255) w Cw (Tg / Ts)0.45 w(Ts, Pw LTs / Tg) (1256) and
H2O: The notation indicates that the emissivities should be evaluated using Ts instead of Tg (both in K or R), Pc LTs / Tg instead of Pc L, and Pw LTs / Tg instead
of Pw L. Note that the absorptivity of the gas depends on the source temperawhen Ts Tg, as exture Ts as well as the gas temperature Tg. Also,
pected. The pressure correction factors Cc and Cw are evaluated using Pc L and
Pw L, as in emissivity calculations.
When the total emissivity of a gas g at temperature Tg is known, the emissive power of the gas (radiation emitted by the gas per unit surface area) can
TABLE 12 – 4
Mean beam length L for various gas volume shapes
Gas Volume Geometry
Hemisphere of radius R radiating to the center of its base
Sphere of diameter D radiating to its surface
Infinite circular cylinder of diameter D radiating to curved surface
Semiinfinite circular cylinder of diameter D radiating to its base
Semiinfinite circular cylinder of diameter D radiating to center
of its base
Infinite semicircular cylinder of radius R radiating to center
of its base
Circular cylinder of height equal to diameter D radiating to
entire surface
Circular cylinder of height equal to diameter D radiating to center
of its base
Infinite slab of thickness D radiating to either bounding plane
Cube of side length L radiating to any face
Arbitrary shape of volume V and surface area As radiating to surface L
R
0.65D
0.95D
0.65D
0.90D
1.26R
0.60D
0.71D
1.80D
0.66L
3.6V /As cen58933_ch12.qxd 9/9/2002 9:49 AM Page 646 646
HEAT TRANSFER
4
be expressed as Eg
g Tg . Then the rate of radiation energy emitted by a
gas to a bounding surface of area As becomes ·
Q g, e g As Tg4 (1257) If the bounding surface is black at temperature Ts, the surface will emit radiation to the gas at a rate of As Ts4 without reflecting any, and the gas will absorb this radiation at a rate of g As Ts4, where g is the absorptivity of the gas.
Then the net rate of radiation heat transfer between the gas and a black surface
surrounding it becomes
·
Q net Black enclosure: As ( gTg4 4
gTs ) (1258) If the surface is not black, the analysis becomes more complicated because
of the radiation reflected by the surface. But for surfaces that are nearly
0.7, Hottel (1954, Ref. 6), recommends this
black with an emissivity s
modification,
·
Q net, gray s 2 1·
Q net, black 1 s 2 As ( gTg4 4
gTs ) (1259) The emissivity of wall surfaces of furnaces and combustion chambers are typically greater than 0.7, and thus the relation above provides great convenience
for preliminary radiation heat transfer calculations. EXAMPLE 12–13 H D 5m A cylindrical furnace whose height and diameter are 5 m contains combustion
gases at 1200 K and a total pressure of 2 atm. The composition of the combustion gases is determined by volumetric analysis to be 80 percent N2, 8 percent H2O, 7 percent O2, and 5 percent CO2. Determine the effective emissivity
of the combustion gases (Fig. 12–39). 5m Tg Effective Emissivity of Combustion Gases 1200 K FIGURE 12–39
Schematic for Example 12–13. SOLUTION The temperature, pressure, and composition of a gas mixture is
given. The emissivity of the mixture is to be determined.
Assumptions 1 All the gases in the mixture are ideal gases. 2 The emissivity
determined is the mean emissivity for radiation emitted to all surfaces of the
cylindrical enclosure.
Analysis The volumetric analysis of a gas mixture gives the mole fractions yi of
the components, which are equivalent to pressure fractions for an ideal gas mixture. Therefore, the partial pressures of CO2 and H2O are
Pc
Pw yCO2 P
yH2O P 0.05(2 atm)
0.08(2 atm) 0.10 atm
0.16 atm The mean beam length for a cylinder of equal diameter and height for radiation
emitted to all surfaces is, from Table 12–4, L 0.60D 0.60(5 m) 3m cen58933_ch12.qxd 9/9/2002 9:49 AM Page 647 647
CHAPTER 12 Then, Pc L
Pw L (0.10 atm)(3 m)
(0.16 atm)(3 m) 0.30 m atm
0.48 m atm 0.98 ft atm
1.57 ft atm The emissivities of CO2 and H2O corresponding to these values at the gas temperature of Tg 1200 K and 1 atm are, from Figure 12–36, 0.16 c, 1 atm and w, 1 atm 0.23 These are the base emissivity values at 1 atm, and they need to be corrected for
the 2 atm total pressure. Noting that (Pw P)/2 (0.16 2)/2 1.08 atm,
the pressure correction factors are, from Figure 12–37, Cc 1.1 and Cw 1.4 Both CO2 and H2O are present in the same mixture, and we need to correct for
the overlap of emission bands. The emissivity correction factor at T
Tg
1200 K is, from Figure 12–38, Pc L Pw L
Pw
Pw Pc 0.98 1.57 0.16
0.16 0.10 2.55
0.048 0.615 Then the effective emissivity of the combustion gases becomes
g Cc c, 1 atm Cw w, 1 atm 1.1 0.16 1.4 0.23 0.048 0.45 Discussion This is the average emissivity for radiation emitted to all surfaces
of the cylindrical enclosure. For radiation emitted towards the center of the
base, the mean beam length is 0.71D instead of 0.60D, and the emissivity
value would be different. EXAMPLE 12–14 Radiation Heat Transfer in a Cylindrical Furnace Reconsider the cylindrical furnace discussed in Example 12–13. For a wall
temperature of 600 K, determine the absorptivity of the combustion gases and
the rate of radiation heat transfer from the combustion gases to the furnace
walls (Fig. 12–40). H Tg
D 1200 K Ts SOLUTION The temperatures for the wall surfaces and the combustion gases
are given for a cylindrical furnace. The absorptivity of the gas mixture and the
rate of radiation heat transfer are to be determined.
Assumptions 1 All the gases in the mixture are ideal gases. 2 All interior
surfaces of furnace walls are black. 3 Scattering by soot and other particles is
negligible.
Analysis The average emissivity of the combustion gases at the gas temperature of Tg 1200 K was determined in the preceding example to be g 0.45. 5m 600 K 5m ·
Qnet FIGURE 12–40
Schematic for Example 12–14. cen58933_ch12.qxd 9/9/2002 9:49 AM Page 648 648
HEAT TRANSFER For a source temperature of Ts
600 K, the absorptivity of the gas is again
determined using the emissivity charts as Pc L Ts
Tg (0.10 atm)(3 m) 600 K
1200 K 0.15 m atm 0.49 ft atm Pw L Ts
Tg (0.16 atm)(3 m) 600 K
1200 K 0.24 m atm 0.79 ft atm The emissivities of CO2 and H2O corresponding to these values at a temperature
of Ts 600 K and 1 atm are, from Figure 12–36, 0.11 c, 1 atm and 0.25 w, 1 atm The pressure correction factors were determined in the preceding example to be
Cc 1.1 and Cw 1.4, and they do not change with surface temperature. Then
the absorptivities of CO2 and H2O become Tg 0.65
Ts
Tg 0.45
Cw
Ts
Cc c w c, 1 atm w, 1 atm (1.1) 1200 K
600 K (1.4) 1200 K
600 K 0.65 (0.11) 0.19 0.45 (0.25) 0.48 Also
, but the emissivity correction factor is to be evaluated from
Figure 12–38 at T
Ts
600 K instead of Tg
1200 K. There is no chart
for 600 K in the figure, but we can read
values at 400 K and 800 K, and
take their average. At Pw /(Pw
Pc)
0.615 and Pc L
Pw L
2.55 we read
0.027. Then the absorptivity of the combustion gases becomes
g c 0.19 w 0.48 0.027 0.64 The surface area of the cylindrical surface is As DH 2 D2
4 (5 m)(5 m) 2 (5 m)2
4 118 m2 Then the net rate of radiation heat transfer from the combustion gases to the
walls of the furnace becomes ·
Q net 4
As ( gTg4
g Ts )
(118 m2)(5.67 10
2.79 104 W 8 W/m2 K4)[0.45(1200 K)4 0.64(600 K)4] Discussion The heat transfer rate determined above is for the case of black
wall surfaces. If the surfaces are not black but the surface emissivity s is
greater than 0.7, the heat transfer rate can be determined by multiplying the
rate of heat transfer already determined by ( s 1)/2. cen58933_ch12.qxd 9/9/2002 9:49 AM Page 649 649
CHAPTER 12 TOPIC OF SPECIAL INTEREST* Heat Transfer from the Human Body
The metabolic heat generated in the body is dissipated to the environment
through the skin and the lungs by convection and radiation as sensible heat
and by evaporation as latent heat (Fig. 12–41). Latent heat represents the
heat of vaporization of water as it evaporates in the lungs and on the skin
by absorbing body heat, and latent heat is released as the moisture condenses on cold surfaces. The warming of the inhaled air represents sensible
heat transfer in the lungs and is proportional to the temperature rise of
inhaled air. The total rate of heat loss from the body can be expressed as
·
Q body, total ·
·
Q skin Q lungs
·
·
(Q sensible Q latent)skin
·
·
(Q convection Q radiation ·
·
(Q sensible Q latent)lungs
·
·
Q latent)skin (Q convection hconv Aclothing(Tclothing Tambient)
hrad Aclothing(Tclothing Tsurr) (W) (1261)
(1262) where
hconv
hrad
Aclothing
Tclothing
Tambient
Tsurr convection heat transfer coefficient, as given in Table 12–5
radiation heat transfer coefficient, 4.7 W/m2 · °C for typical indoor
conditions; the emissivity is assumed to be 0.95, which is typical
outer surface area of a clothed person
average temperature of exposed skin and clothing
ambient air temperature
average temperature of the surrounding surfaces *This section can be skipped without a loss in continuity. Evaporation
30% Radiation
40% Air
motion Conduction
3% ·
Q latent)lungs (1260) Therefore, the determination of heat transfer from the body by analysis
alone is difficult. Clothing further complicates the heat transfer from the
body, and thus we must rely on experimental data. Under steady conditions, the total rate of heat transfer from the body is equal to the rate of
metabolic heat generation in the body, which varies from about 100 W for
light office work to roughly 1000 W during heavy physical work.
Sensible heat loss from the skin depends on the temperatures of the skin,
the environment, and the surrounding surfaces as well as the air motion.
The latent heat loss, on the other hand, depends on the skin wettedness and
the relative humidity of the environment as well. Clothing serves as insulation and reduces both the sensible and latent forms of heat loss. The heat
transfer from the lungs through respiration obviously depends on the frequency of breathing and the volume of the lungs as well as the environmental factors that affect heat transfer from the skin.
Sensible heat from the clothed skin is first transferred to the clothing and
then from the clothing to the environment. The convection and radiation
heat losses from the outer surface of a clothed body can be expressed as
·
Q conv
·
Q rad Convection
27% Floor FIGURE 12–41
Mechanisms of heat loss
from the human body and relative
magnitudes for a resting person. cen58933_ch12.qxd 9/9/2002 9:49 AM Page 650 TABLE 12 – 5
Convection heat transfer coefficients
for a clothed body at 1 atm
( is in m/s) (compiled
from various sources)
hconv,*
W/m2 · °C Activity Seated in air moving at
0
0.2 m/s
3.1
0.2
4 m/s
8.3
Walking in still air at
0.5
2 m/s
8.6
Walking on treadmill
in still air at
0.5
2 m/s
6.5
Standing in moving air at
0
0.15 m/s
4.0
0.15
1.5 m/s 14.8 0.6 0.53 The convection heat transfer coefficients at 1 atm pressure are given in
Table 12–5. Convection coefficients at pressures P other than 1 atm are
obtained by multiplying the values at atmospheric pressure by P 0.55 where
P is in atm. Also, it is recognized that the temperatures of different surfaces
surrounding a person are probably different, and Tsurr represents the mean
radiation temperature, which is the temperature of an imaginary isothermal enclosure in which radiation heat exchange with the human body
equals the radiation heat exchange with the actual enclosure. Noting that
most clothing and building materials are essentially black, the mean radiation temperature of an enclosure that consists of N surfaces at different
temperatures can be determined from
Tsurr 0.39 0.69 *At pressures other than 1 atm, multiply by
P 0.55, where P is in atm. Fperson1 T1 Fperson2 T2 ···· FpersonN TN (1263) where Ti is the temperature of the surface i and Fpersoni is the view factor
between the person and surface i.
Total sensible heat loss can also be expressed conveniently by combining the convection and radiation heat losses as
·
Q conv rad hcombined Aclothing (Tclothing Toperative)
(hconv hrad)Aclothing (Tclothing Toperative) (W) (1264)
(1265) Tsurr
·
Qrad
·
Qconv Tambient (a) Convection and radiation, separate Toperative
·
Qconv + rad (b) Convection and radiation, combined FIGURE 12–42
Heat loss by convection and radiation
from the body can be combined
into a single term by defining an
equivalent operative temperature. 650 where the operative temperature Toperative is the average of the mean radiant and ambient temperatures weighed by their respective convection and
radiation heat transfer coefficients and is expressed as (Fig. 12–42)
Toperative hconv Tambient hrad Tsurr
hconv hrad Tambient Tsurr
2 (1266) Note that the operative temperature will be the arithmetic average of the
ambient and surrounding surface temperatures when the convection and
radiation heat transfer coefficients are equal to each other. Another environmental index used in thermal comfort analysis is the effective temperature, which combines the effects of temperature and humidity. Two
environments with the same effective temperature will evoke the same
thermal response in people even though they are at different temperatures
and humidities.
Heat transfer through the clothing can be expressed as
·
Q conv rad Aclothing (Tskin Tclothing)
Rclothing (1267) where Rclothing is the unit thermal resistance of clothing in m2 · °C/W,
which involves the combined effects of conduction, convection, and radiation between the skin and the outer surface of clothing. The thermal
resistance of clothing is usually expressed in the unit clo where 1 clo
0.155 m2 · °C/W 0.880 ft2 · °F · h/Btu. The thermal resistance of trousers,
longsleeve shirt, longsleeve sweater, and Tshirt is 1.0 clo, or 0.155
m2 · °C/W. Summer clothing such as light slacks and shortsleeved shirt has
an insulation value of 0.5 clo, whereas winter clothing such as heavy
slacks, longsleeve shirt, and a sweater or jacket has an insulation value of
0.9 clo. cen58933_ch12.qxd 9/9/2002 9:49 AM Page 651 651
CHAPTER 12 Then the total sensible heat loss can be expressed in terms of the
skin temperature instead of the inconvenient clothing temperature as
(Fig. 12–43)
·
Q conv Aclothing (Tskin Toperative)
1 rad Rclothing Tcloth
Toperative (1268)
Rcombined hcombined Rcloth At a state of thermal comfort, the average skin temperature of the body is
observed to be 33°C (91.5°F). No discomfort is experienced as the skin
temperature fluctuates by 1.5°C (2.5°F). This is the case whether the
body is clothed or unclothed.
Evaporative or latent heat loss from the skin is proportional to the difference between the water vapor pressure at the skin and the ambient air,
and the skin wettedness, which is a measure of the amount of moisture on
the skin. It is due to the combined effects of the evaporation of sweat and
the diffusion of water through the skin, and can be expressed as
·
Q latent ·
m vapor hfg Skin
Tskin FIGURE 12–43
Simplified thermal resistance
network for heat transfer
from a clothed person. (1269) where
·
m vapor
hf g the rate of evaporation from the body, kg/s
the enthalpy of vaporization of water 2430 kJ/kg at 30°C Heat loss by evaporation is maximum when the skin is completely wetted.
Also, clothing offers resistance to evaporation, and the rate of evaporation
in clothed bodies depends on the moisture permeability of the clothes. The
maximum evaporation rate for an average man is about 1 L/h (0.3 g/s),
which represents an upper limit of 730 W for the evaporative cooling rate.
A person can lose as much as 2 kg of water per hour during a workout on a
hot day, but any excess sweat slides off the skin surface without evaporating (Fig. 12–44).
During respiration, the inhaled air enters at ambient conditions and exhaled air leaves nearly saturated at a temperature close to the deep body
temperature (Fig. 12–45). Therefore, the body loses both sensible heat by
convection and latent heat by evaporation from the lungs, and these can be
expressed as
·
Q conv, lungs
·
Q latent, lungs ·
m air, lungs Cp, air(Texhale Tambient)
·
·
m vapor, lungs hfg m air, lungs (wexhale ·
mvapor, max = 0.3 g/s (1270) wambient)hfg where
·
m air, lungs
Cp, air
Texhale
w Water
vapor rate of air intake to the lungs, kg/s
specific heat of air 1.0 kJ/kg · °C
temperature of exhaled air
humidity ratio (the mass of moisture per unit mass of dry air) (1271)
·
·
Qlatent, max = mlatent, max hfg @ 30°C
= (0.3 g/s)(2430 kJ/kg)
= 730 W FIGURE 12–44
An average person can lose heat at
a rate of up to 730 W by evaporation. cen58933_ch12.qxd 9/9/2002 9:49 AM Page 652 652
HEAT TRANSFER
Cool
ambient air
20°C Warm and moist
exhaled air
35°C 37°C The rate of air intake to the lungs is directly proportional to the metabolic
·
rate Q met. The rate of total heat loss from the lungs through respiration can
be expressed approximately as
·
Q conv latent, lungs ·
0.0014Q met (34 Tambient) ·
0.0173Q met (5.87 P , ambient) (1272) where P , ambient is the vapor pressure of ambient air in kPa.
The fraction of sensible heat varies from about 40 percent in the case of
heavy work to about 70 percent during light work. The rest of the energy is
rejected from the body by perspiration in the form of latent heat. Lungs
Heat and
moisture EXAMPLE 12–15
FIGURE 12–45
Part of the metabolic heat generated in
the body is rejected to the air from
the lungs during respiration. Effect of Clothing on Thermal Comfort It is well established that a clothed or unclothed person feels comfortable when
the skin temperature is about 33°C. Consider an average man wearing summer
clothes whose thermal resistance is 0.6 clo. The man feels very comfortable
while standing in a room maintained at 22°C. The air motion in the room is negligible, and the interior surface temperature of the room is about the same as
the air temperature. If this man were to stand in that room unclothed, determine the temperature at which the room must be maintained for him to feel
thermally comfortable. SOLUTION A man wearing summer clothes feels comfortable in a room at
22°C. The room temperature at which this man would feel thermally comfortable when unclothed is to be determined.
Assumptions 1 Steady conditions exist. 2 The latent heat loss from the person
remains the same. 3 The heat transfer coefficients remain the same.
Analysis The body loses heat in sensible and latent forms, and the sensible
heat consists of convection and radiation heat transfer. At low air velocities, the
convection heat transfer coefficient for a standing man is given in Table 12–5
to be 4.0 W/m2 · °C. The radiation heat transfer coefficient at typical indoor
conditions is 4.7 W/m2 · °C. Therefore, the surface heat transfer coefficient for
a standing person for combined convection and radiation is
22°C 22°C hcombined hconv hrad 4.0 4.7 8.7 W/m2 · °C The thermal resistance of the clothing is given to be Rclothing
33°C 0.6 clo 0.6 0.155 m2 · °C/W 0.093 m2 · °C/W Noting that the surface area of an average man is 1.8 m2, the sensible heat loss
from this person when clothed is determined to be (Fig. 12–46) ·
Q sensible, clothed As(Tskin
Rclothing Tambient)
1
hcombined (1.8 m2)(33
0.093 m2 · °C/ W 22)°C
1
8.7 W/m2 · °C 95.2 W FIGURE 12–46
Schematic for Example 12–15. From a heat transfer point of view, taking the clothes off is equivalent to removing the clothing insulation or setting Rcloth
0. The heat transfer in this
case can be expressed as cen58933_ch12.qxd 9/9/2002 9:49 AM Page 653 653
CHAPTER 12 ·
Q sensible, unclothed As(Tskin Tambient) (1.8 m2)(33 1 Tambient)°C Troom = 22°C 1
8.7 W/m2 · °C hcombined Troom = 27°C Tskin = 33°C Tskin = 33°C To maintain thermal comfort after taking the clothes off, the skin temperature
of the person and the rate of heat transfer from him must remain the same.
Then setting the equation above equal to 95.2 W gives Tambient 26.9°C Clothed
person Therefore, the air temperature needs to be raised from 22 to 26.9°C to ensure
that the person will feel comfortable in the room after he takes his clothes off
(Fig. 12–47). Note that the effect of clothing on latent heat is assumed to be
negligible in the solution above. We also assumed the surface area of the
clothed and unclothed person to be the same for simplicity, and these two
effects should counteract each other. Unclothed
person FIGURE 12–47
Clothing serves as insulation,
and the room temperature needs to be
raised when a person is unclothed to
maintain the same comfort level. SUMMARY
Radiaton heat transfer between surfaces depends on the orientation of the surfaces relative to each other, the effects of
orientation are accounted for by the geometric parameter view
factor. The view factor from a surface i to a surface j is denoted
by Fi → j or Fij, and is defined as the fraction of the radiation
leaving surface i that strikes surface j directly. The view factors
between differential and finite surfaces are expressed as differential view factor dFdA1 → dA2 is expressed as
dFdA1 → dA2 ·
Q dA1 → dA2
·
Q cos dA1 FdA1 → A2
F12 F A1 → A2 cos
A2 1 cos
r2 ·
Q A1 → A2
·
Q
A1 1
A1 2 1 cos
r2 dA2 The net radiation heat transfer from any surface i of a black
enclosure is determined by adding up the net radiation heat
transfers from surface i to each of the surfaces of the enclosure: dA2
cos A2 2 A1 1 cos
r2 2 dA1 dA2 where r is the distance between dA1 and dA2, and 1 and 2 are
the angles between the normals of the surfaces and the line that
connects dA1 and dA2.
The view factor Fi → i represents the fraction of the radiation
leaving surface i that strikes itself directly; Fi → i 0 for plane
0 for concave surfaces. For
or convex surfaces and Fi → i
view factors, the reciprocity rule is expressed as
Ai Fi → j unity. This is known as the summation rule for an enclosure.
The superposition rule is expressed as the view factor from a
surface i to a surface j is equal to the sum of the view factors
from surface i to the parts of surface j. The symmetry rule is
expressed as if the surfaces j and k are symmetric about the
surface i then Fi → j Fi → k.
The rate of net radiation heat transfer between two black surfaces is determined from
·
Q 1 → 2 A1 F1 → 2 (T14 T24)
(W) Aj Fj → i The sum of the view factors from surface i of an enclosure to
all surfaces of the enclosure, including to itself, must equal N ·
Qi
j N ·
Qi → j
1 Ai Fi → j (Ti4
j Tj4) (W) 1 The total radiation energy leaving a surface per unit time and
per unit area is called the radiosity and is denoted by J. The
net rate of radiation heat transfer from a surface i of surface
area Ai is expressed as
·
Qi Ebi Ji (W) Ri where
Ri 1
Ai i
i cen58933_ch12.qxd 9/9/2002 9:49 AM Page 654 654
HEAT TRANSFER is the surface resistance to radiation. The net rate of radiation
heat transfer from surface i to surface j can be expressed as Ji Jj
Ri → j ·
Qi → j 1
Ai Fi → j is the space resistance to radiation. The network method is
applied to radiation enclosure problems by drawing a surface
resistance associated with each surface of an enclosure and
connecting them with space resistances. Then the problem is
solved by treating it as an electrical network problem where the
radiation heat transfer replaces the current and the radiosity
replaces the potential. The direct method is based on the
following two equations:
N Surfaces with specified
·
· Qi
net heat transfer rate Q i Ai Fi → j(Ji
j Jj) Ti4 L e ·
Q 12 1
A1 i
i Fi → j(Ji
j Jj) 1 T24)
1
A2 1
A1 F12 1
1 A (T14
1 1 1 2 (W) ··· (K) 1 e L , and L e where is the spectral absorption coefficient of the medium.
The emissivities of H2O and CO2 gases are given in Figure
12–36 for a total pressure of P 1 atm. Emissivities at other
pressures are determined from
Cw and w, 1 atm Cc c c, 1 atm where Cw and Cc are the pressure correction factors. For gas
mixtures that contain both of H2O and CO2, the emissivity is
determined from
g c T24)
1 3, 1 3, 2 1 1 N, 1 N, 2 1 1 Cc w Cw c, 1 atm w, 1 atm where
is the emissivity correction factor, which accounts
for the overlap of emission bands. The gas absorptivities for radiation emitted by a source at temperature Ts are determined
similarly from
g where
CO2:
H2O: 2 1 1 1 c w at the source temperature Ts and 2 Radiation heat transfer between two surfaces can be reduced
greatly by inserting between the two surfaces thin, highreflectivity (lowemissivity) sheets of material called radiation shields. Radiation heat transfer between two large
parallel plates separated by N radiation shields is
·
Q 12, N shields 4
Tw ) N The first group (for surfaces with specified heat transfer rates)
and the second group (for surfaces with specified temperatures) of equations give N linear algebraic equations for the determination of the N unknown radiosities for an Nsurface
enclosure. Once the radiosities J1, J2, . . . , JN are available, the
unknown surface temperatures and heat transfer rates can be
determined from the equations just shown.
The net rate of radiation transfer between any two gray, diffuse, opaque surfaces that form an enclosure is given by
(T14 ,
1 1 1 Ji 4
(Tth
h where Tf is the actual temperature of the fluid, Tth is the temperature value measured by the thermometer, and Tw is the
temperature of the surrounding walls, all in K.
Gases with asymmetric molecules such as H2O, CO2 CO,
SO2, and hydrocarbons HnCm participate in the radiation process by absorption and emission. The spectral transmissivity,
absorptivity, and emissivity of a medium are expressed as w Surfaces with specified
temperature Ti th Tth Tf (W) where
Ri → j The radiation effect in temperature measurements can be properly accounted for by the relation c
w Cc
Cw (Tg / Ts)0.65
(Tg / Ts)0.45 c(Ts, Pc LTs / Tg)
(Ts, Pw LTs / Tg)
w The rate of radiation heat transfer between a gas and a surrounding surface is
Black enclosure:
Gray enclosure,
with s 0.7: ·
Q net
·
Q net, gray As ( gTg4
1 s 2 4
gTs ) As ( gTg4 4
gTs ) cen58933_ch12.qxd 9/9/2002 9:49 AM Page 655 655
CHAPTER 12 REFERENCES AND SUGGESTED READING
1. D. K. Edwards. Radiation Heat Transfer Notes.
Washington, D.C.: Hemisphere, 1981.
2. D. K. Edwards and R. Matavosian. “Scaling Rules for
Total Absorptivity and Emissivity of Gases.” Journal
of Heat Transfer 106 (1984), pp. 684–689. 8. H. C. Hottel and R. B. Egbert. “Radiant Heat
Transmission from Water Vapor.” Transactions of
the AIChE 38 (1942), pp. 531–565.
9. J. R. Howell. A Catalog of Radiation Configuration
Factors. New York: McGrawHill, 1982. 3. D. K. Edwards and R. Matavosian. “Emissivity Data for
Gases.” Section 5.5.5, in Hemisphere Handbook of
Heat Exchanger Design, ed. G. F. Hewitt. New York:
Hemisphere, 1990. 10. F. P. Incropera and D. P. DeWitt. Introduction to Heat
Transfer. 4th ed. New York: John Wiley & Sons, 2002. 4. D. C. Hamilton and W. R. Morgan. “Radiation
Interchange Configuration Factors.” National Advisory
Committee for Aeronautics, Technical Note 2836, 1952. 12. M. F. Modest. Radiative Heat Transfer. New York:
McGrawHill, 1993. 11. F. Kreith and M. S. Bohn. Principles of Heat Transfer.
6th ed. Pacific Grove, CA: Brooks/Cole, 2001. 5. J. P. Holman. Heat Transfer. 9th ed. New York:
McGrawHill, 2002. 13. A. K. Oppenheim. “Radiation Analysis by the Network
Method.” Transactions of the ASME 78 (1956),
pp. 725–735. 6. H. C. Hottel. “Radiant Heat Transmission.” In Heat
Transmission, ed. W. H. McAdams. 3rd ed. New York:
McGrawHill, 1954. 14. R. Siegel and J. R. Howell. Thermal Radiation Heat
Transfer. 3rd ed. Washington, D.C.: Hemisphere, 1992. 7. H. C. Hottel. “Heat Transmission by Radiation from
Nonluminous Gases,” Transaction of the AIChE (1927),
pp. 173–205. 15. N. V. Suryanaraya. Engineering Heat Transfer. St. Paul,
Minn.: West, 1995. PROBLEMS*
The View Factor
12–1C What does the view factor represent? When is the
view factor from a surface to itself not zero?
12–2C How can you determine the view factor F12 when the
view factor F21 and the surface areas are available? 12–6 Consider an enclosure consisting of five surfaces. How
many view factors does this geometry involve? How many
of these view factors can be determined by the application of
the reciprocity and summation rules? 12–3C What are the summation rule and the superposition
rule for view factors? 12–7 Consider an enclosure consisting of 12 surfaces. How
many view factors does this geometry involve? How many of
these view factors can be determined by the application of the
reciprocity and the summation rules?
Answers: 144, 78 12–4C What is the crossedstrings method? For what kind of
geometries is the crossedstrings method applicable? 12–8 Determine the view factors F13 and F23 between the
rectangular surfaces shown in Figure P12–8. 12–5 Consider an enclosure consisting of six surfaces. How
many view factors does this geometry involve? How many
of these view factors can be determined by the application of
the reciprocity and the summation rules? 2m
1m A1
*Problems designated by a “C” are concept questions, and
students are encouraged to answer them all. Problems designated
by an “E” are in English units, and the SI users can ignore them.
Problems with an EESCD icon
are solved using EES, and
complete solutions together with parametric studies are included
on the enclosed CD. Problems with a computerEES icon
are
comprehensive in nature, and are intended to be solved with a
computer, preferably using the EES software that accompanies
this text. A2 1m
A3 1m FIGURE P12–8
12–9 Consider a cylindrical enclosure whose height is twice
the diameter of its base. Determine the view factor from the
side surface of this cylindrical enclosure to its base surface. cen58933_ch12.qxd 9/9/2002 9:49 AM Page 656 656
HEAT TRANSFER b
2
3 FIGURE P12–11
(a) Semicylindrical duct.
(b) Triangular duct.
(c) Rectangular duct. 2 2 b 50° 1 50° 1 a 1 a D
(a) (b) (c) a D b b b a
(a) (b) (c) FIGURE P12–12
(a) Semicylindrical groove.
(b) Triangular groove.
(c) Rectangular groove.
12–10 Consider a hemispherical furnace with a flat circular
base of diameter D. Determine the view factor from the dome
Answer: 0.5
of this furnace to its base. 12–15 Determine the four view factors associated with an enclosure formed by two very long concentric cylinders of radii
r1 and r2. Neglect the end effects. 12–11 Determine the view factors F12 and F21 for the very
long ducts shown in Figure P12–11 without using any view
factor tables or charts. Neglect end effects. 12–16 Determine the view factor F12 between the rectangular
surfaces shown in Figure P12–16. 12–12 Determine the view factors from the very long
grooves shown in Figure P12–12 to the surroundings without
using any view factor tables or charts. Neglect end effects.
12–13 Determine the view factors from the base of a cube to
each of the other five surfaces.
12–14 Consider a conical enclosure of height h and base diameter D. Determine the view factor from the conical side surface to a hole of diameter d located at the center of the base. 12–17 Two infinitely long parallel cylinders of diameter D
are located a distance s apart from each other. Determine the
view factor F12 between these two cylinders.
12–18 Three infinitely long parallel cylinders of diameter D
are located a distance s apart from each other. Determine the
view factor between the cylinder in the middle and the surroundings. h
1
s
d
D FIGURE P12–14 s D
D D FIGURE P12–18 cen58933_ch12.qxd 9/9/2002 9:49 AM Page 657 657
CHAPTER 12
1
1m 1m 1 1m 1 1m 2m
1m 1m 1m 1m 2 1m 1m
3m (a) 2m 1m
2 1m 3m
(b) 2
2m FIGURE P12–16 (c) Radiation Heat Transfer between Surfaces
12–19C Why is the radiation analysis of enclosures that consist of black surfaces relatively easy? How is the rate of radiation heat transfer between two surfaces expressed in this case?
12–20C How does radiosity for a surface differ from the
emitted energy? For what kind of surfaces are these two quantities identical? ture vary from 500 K to 1000 K and the emissivity from 0.1 to
0.9. Plot the net rate of radiation heat transfer as functions of
temperature and emissivity, and discuss the results.
12–28 A furnace is of cylindrical shape with R H 2 m.
The base, top, and side surfaces of the furnace are all black and
are maintained at uniform temperatures of 500, 700, and 1200
K, respectively. Determine the net rate of radiation heat transfer to or from the top surface during steady operation. 12–21C What are the radiation surface and space resistances? How are they expressed? For what kind of surfaces is
the radiation surface resistance zero?
12–22C What are the two methods used in radiation analysis? How do these two methods differ? 1
3 12–23C What is a reradiating surface? What simplifications
does a reradiating surface offer in the radiation analysis?
12–24E Consider a 10ft
10ft
10ft cubical furnace
whose top and side surfaces closely approximate black surfaces and whose base surface has an emissivity
0.7. The
base, top, and side surfaces of the furnace are maintained at
uniform temperatures of 800 R, 1600 R, and 2400 R, respectively. Determine the net rate of radiation heat transfer between
(a) the base and the side surfaces and (b) the base and the top
surfaces. Also, determine the net rate of radiation heat transfer
to the base surface.
Reconsider Problem 12–24E. Using EES (or
other) software, investigate the effect of base
surface emissivity on the net rates of radiation heat transfer between the base and the side surfaces, between the base and top
surfaces, and to the base surface. Let the emissivity vary from
0.1 to 0.9. Plot the rates of heat transfer as a function of emissivity, and discuss the results. H=2n
R=2m 2 FIGURE P12–28
12–29 Consider a hemispherical furnace of diameter D 5
m with a flat base. The dome of the furnace is black, and the
base has an emissivity of 0.7. The base and the dome of the furnace are maintained at uniform temperatures of 400 and 1000
K, respectively. Determine the net rate of radiation heat transfer from the dome to the base surface during steady operation.
Answer: 759 kW 12–25E 12–26 Two very large parallel plates are maintained at uniform temperatures of T1 600 K and T2 400 K and have
emissivities 1 0.5 and 2 0.9, respectively. Determine the
net rate of radiation heat transfer between the two surfaces per
unit area of the plates.
12–27 Reconsider Problem 12–26. Using EES (or
other) software, investigate the effects of the
temperature and the emissivity of the hot plate on the net rate
of radiation heat transfer between the plates. Let the tempera Black
2
1 ε = 0.7
5m FIGURE P12–29
12–30 Two very long concentric cylinders of diameters D1
0.2 m and D2 0.5 m are maintained at uniform temperatures
of T1 950 K and T2 500 K and have emissivities 1 1
and 2 0.7, respectively. Determine the net rate of radiation
heat transfer between the two cylinders per unit length of the
cylinders.
12–31 This experiment is conducted to determine the emissivity of a certain material. A long cylindrical rod of diameter cen58933_ch12.qxd 9/9/2002 9:49 AM Page 658 658
HEAT TRANSFER D1 0.01 m is coated with this new material and is placed in
an evacuated long cylindrical enclosure of diameter D2
0.1 m and emissivity 2 0.95, which is cooled externally and
maintained at a temperature of 200 K at all times. The rod is
heated by passing electric current through it. When steady operating conditions are reached, it is observed that the rod is dissipating electric power at a rate of 8 W per unit of its length
and its surface temperature is 500 K. Based on these measurements, determine the emissivity of the coating on the rod.
12–32E A furnace is shaped like a long semicylindrical duct
of diameter D 15 ft. The base and the dome of the furnace
have emissivities of 0.5 and 0.9 and are maintained at uniform
temperatures of 550 and 1800 R, respectively. Determine the
net rate of radiation heat transfer from the dome to the base
surface per unit length during steady operation. 1 the net rate of radiation heat transfer between the floor and the
ceiling of the furnace.
12–37 Two concentric spheres of diameters D1
0.3 m
0.8 m are maintained at uniform temperatures
and D2
T1 700 K and T2 400 K and have emissivities 1 0.5 and
0.7, respectively. Determine the net rate of radiation heat
2
transfer between the two spheres. Also, determine the convection heat transfer coefficient at the outer surface if both the surrounding medium and the surrounding surfaces are at 30°C.
Assume the emissivity of the outer surface is 0.35.
12–38 A spherical tank of diameter D
2 m that is filled
with liquid nitrogen at 100 K is kept in an evacuated cubic enclosure whose sides are 3 m long. The emissivities of the
spherical tank and the enclosure are 1
0.1 and 2
0.8,
respectively. If the temperature of the cubic enclosure is measured to be 240 K, determine the net rate of radiation heat
Answer: 228 W
transfer to the liquid nitrogen.
2 D = 15 ft Liquid
N2 FIGURE P12–32E
12–33 Two parallel disks of diameter D 0.6 m separated
by L 0.4 m are located directly on top of each other. Both
disks are black and are maintained at a temperature of 700 K.
The back sides of the disks are insulated, and the environment
that the disks are in can be considered to be a blackbody at
300 K. Determine the net rate of radiation heat transfer
T
Answer: 5505 W
from the disks to the environment.
12–34 A furnace is shaped like a long equilateraltriangular
duct where the width of each side is 2 m. Heat is supplied from
0.8, at a rate of
the base surface, whose emissivity is 1
800 W/m2 while the side surfaces, whose emissivities are 0.5,
are maintained at 500 K. Neglecting the end effects, determine
the temperature of the base surface. Can you treat this geometry as a twosurface enclosure?
12–35 Reconsider Problem 12–34. Using EES (or
other) software, investigate the effects of the
rate of the heat transfer at the base surface and the temperature
of the side surfaces on the temperature of the base surface. Let
the rate of heat transfer vary from 500 W/m2 to 1000 W/m2 and
the temperature from 300 K to 700 K. Plot the temperature of
the base surface as functions of the rate of heat transfer and the
temperature of the side surfaces, and discuss the results.
12–36 Consider a 4m 4m 4m cubical furnace whose
floor and ceiling are black and whose side surfaces are reradiating. The floor and the ceiling of the furnace are maintained at
temperatures of 550 K and 1100 K, respectively. Determine FIGURE P12–38
12–39 Repeat Problem 12–38 by replacing the cubic enclosure by a spherical enclosure whose diameter is 3 m.
12–40 Reconsider Problem 12–38. Using EES (or
other) software, investigate the effects of the
side length and the emissivity of the cubic enclosure, and the
emissivity of the spherical tank on the net rate of radiation heat
transfer. Let the side length vary from 2.5 m to 5.0 m and both
emissivities from 0.1 to 0.9. Plot the net rate of radiation heat
transfer as functions of side length and emissivities, and discuss the results.
12–41 Consider a circular grill whose diameter is 0.3 m. The
bottom of the grill is covered with hot coal bricks at 1100 K,
while the wire mesh on top of the grill is covered with steaks
initially at 5°C. The distance between the coal bricks and the
steaks is 0.20 m. Treating both the steaks and the coal bricks as
blackbodies, determine the initial rate of radiation heat transfer
from the coal bricks to the steaks. Also, determine the initial
rate of radiation heat transfer to the steaks if the side opening
of the grill is covered by aluminum foil, which can be approximated as a reradiating surface.
Answers: 1674 W, 3757 W cen58933_ch12.qxd 9/9/2002 9:49 AM Page 659 659
CHAPTER 12
Steaks
T2 = 275 K
ε2 = 1 3 T3 = 300 K
ε3 = 1
D 0.20 m Coal
bricks D 2 s 1 T1 = 425 K
ε1 = 1 FIGURE P12–44
FIGURE P12–41 12–42E A 19–fthigh room with a base area of 12 ft 12 ft
is to be heated by electric resistance heaters placed on the ceiling, which is maintained at a uniform temperature of 90°F at
all times. The floor of the room is at 65°F and has an emissivity of 0.8. The side surfaces are well insulated. Treating the
ceiling as a blackbody, determine the rate of heat loss from the
room through the floor.
12–43 Consider two rectangular surfaces perpendicular to
each other with a common edge which is 1.6 m long. The horizontal surface is 0.8 m wide and the vertical surface is 1.2 m
high. The horizontal surface has an emissivity of 0.75 and is
maintained at 400 K. The vertical surface is black and is maintained at 550 K. The back sides of the surfaces are insulated.
The surrounding surfaces are at 290 K, and can be considered
to have an emissivity of 0.85. Determine the net rate of radiation heat transfers between the two surfaces, and between the
horizontal surface and the surroundings. T2 = 550 K
ε2 = 1
W = 1.6 m
L2 = 1.2 m
L1 = 0.8 m A2 2 A1 12–45 Consider a long semicylindrical duct of diameter
1.0 m. Heat is supplied from the base surface, which is black,
at a rate of 1200 W/m2, while the side surface with an emissivity of 0.4 are is maintained at 650 K. Neglecting the end effects, determine the temperature of the base surface.
12–46 Consider a 20cmdiameter hemispherical enclosure.
The dome is maintained at 600 K and heat is supplied from the
dome at a rate of 50 W while the base surface with an emissivity is 0.55 is maintained at 400 K. Determine the emissivity of
the dome. Radiation Shields and the Radiation Effect
12–47C What is a radiation shield? Why is it used?
12–48C What is the radiation effect? How does it influence
the temperature measurements?
12–49C Give examples of radiation effects that affect human
comfort.
12–50 Consider a person whose exposed surface area is
1.7 m2, emissivity is 0.85, and surface temperature is 30°C.
Determine the rate of heat loss from that person by radiation in
a large room whose walls are at a temperature of (a) 300 K and
(b) 280 K. 3
T3 = 290 K
ε3 = 0.85 1
T1 = 400 K
ε1 = 0.75 FIGURE P12–43 12–44 Two long parallel 16cmdiameter cylinders are located 50 cm apart from each other. Both cylinders are black,
and are maintained at temperatures 425 K and 275 K. The
surroundings can be treated as a blackbody at 300 K. For a
1mlong section of the cylinders, determine the rates of radiation heat transfer between the cylinders and between the hot
cylinder and the surroundings. 12–51 A thin aluminum sheet with an emissivity of 0.15 on
both sides is placed between two very large parallel plates,
which are maintained at uniform temperatures T1 900 K and
650 K and have emissivities 1
0.5 and 2
0.8,
T2
respectively. Determine the net rate of radiation heat transfer
between the two plates per unit surface area of the plates and
compare the result with that without the shield. 1 T1 = 900 K
ε1 = 0.5 3 ε3 = 0.15 2 T2 = 650 K
ε2 = 0.8 FIGURE P12–51 cen58933_ch12.qxd 9/9/2002 9:49 AM Page 660 660
HEAT TRANSFER 12–52 Reconsider Problem 12–51. Using EES (or
other) software, plot the net rate of radiation
heat transfer between the two plates as a function of the emissivity of the aluminum sheet as the emissivity varies from 0.05
to 0.25, and discuss the results. 12–53 Two very large parallel plates are maintained at uniform temperatures of T1 1000 K and T2 800 K and have
0.2, respectively. It is desired to
emissivities of 1
2
reduce the net rate of radiation heat transfer between the two
plates to onefifth by placing thin aluminum sheets with an
emissivity of 0.15 on both sides between the plates. Determine
the number of sheets that need to be inserted.
12–54 Five identical thin aluminum sheets with emissivities
of 0.1 on both sides are placed between two very large parallel
plates, which are maintained at uniform temperatures of T1
0.1,
800 K and T2 450 K and have emissivities of 1
2
respectively. Determine the net rate of radiation heat transfer
between the two plates per unit surface area of the plates and
compare the result to that without the shield.
12–55 Reconsider Problem 12–54. Using EES (or
other) software, investigate the effects of the
number of the aluminum sheets and the emissivities of the
plates on the net rate of radiation heat transfer between the two
plates. Let the number of sheets vary from 1 to 10 and the
emissivities of the plates from 0.1 to 0.9. Plot the rate of radiation heat transfer as functions of the number of sheets and
the emissivities of the plates, and discuss the results. 12–56E Two parallel disks of diameter D 3 ft separated by
L 2 ft are located directly on top of each other. The disks are
separated by a radiation shield whose emissivity is 0.15. Both
disks are black and are maintained at temperatures of 1200 R
and 700 R, respectively. The environment that the disks are in
can be considered to be a blackbody at 540 R. Determine the
net rate of radiation heat transfer through the shield under
Answer: 866 Btu/h
steady conditions. 12–57 A radiation shield that has the same emissivity 3 on
both sides is placed between two large parallel plates, which
650 K and
are maintained at uniform temperatures of T1
T2 400 K and have emissivities of 1 0.6 and 2 0.9,
respectively. Determine the emissivity of the radiation shield if
the radiation heat transfer between the plates is to be reduced to
15 percent of that without the radiation shield.
12–58 Reconsider Problem 12–57. Using EES (or
other) software, investigate the effect of the percent reduction in the net rate of radiation heat transfer between
the plates on the emissivity of the radiation shields. Let the percent reduction vary from 40 to 95 percent. Plot the emissivity
versus the percent reduction in heat transfer, and discuss the
results. 12–59 Two coaxial cylinders of diameters D1 0.10 m and
D2 0.30 m and emissivities 1 0.7 and 2 0.4 are maintained at uniform temperatures of T1 750 K and T2 500 K,
respectively. Now a coaxial radiation shield of diameter D3
0.2 is placed between the two
0.20 m and emissivity 3
cylinders. Determine the net rate of radiation heat transfer between the two cylinders per unit length of the cylinders and
compare the result with that without the shield.
12–60 Reconsider Problem 12–59. Using EES (or
other) software, investigate the effects of the diameter of the outer cylinder and the emissivity of the radiation
shield on the net rate of radiation heat transfer between the two
cylinders. Let the diameter vary from 0.25 m to 0.50 m and the
emissivity from 0.05 to 0.35. Plot the rate of radiation heat
transfer as functions of the diameter and the emissivity, and
discuss the results. Radiation Exchange with Absorbing and Emitting Gases
12–61C How does radiation transfer through a participating
medium differ from that through a nonparticipating medium?
12–62C Define spectral transmissivity of a medium of thickness L in terms of (a) spectral intensities and (b) the spectral
absorption coefficient.
12–63C Define spectral emissivity of a medium of thickness
L in terms of the spectral absorption coefficient. 1 T1 = 1200 R
1 ft 3 ε3 = 0.15
1 ft 2 T2 = 700 R FIGURE P12–56E 12–64C How does the wavelength distribution of radiation
emitted by a gas differ from that of a surface at the same temperature?
12–65 Consider an equimolar mixture of CO2 and O2 gases at
500 K and a total pressure of 0.5 atm. For a path length of
1.2 m, determine the emissivity of the gas.
12–66 A cubic furnace whose side length is 6 m contains
combustion gases at 1000 K and a total pressure of 1 atm. The
composition of the combustion gases is 75 percent N2, 9 percent H2O, 6 percent O2, and 10 percent CO2. Determine the
effective emissivity of the combustion gases. cen58933_ch12.qxd 9/9/2002 9:49 AM Page 661 661
CHAPTER 12 12–67 A cylindrical container whose height and diameter are
8 m is filled with a mixture of CO2 and N2 gases at 600 K and
1 atm. The partial pressure of CO2 in the mixture is 0.15 atm.
If the walls are black at a temperature of 450 K, determine
the rate of radiation heat transfer between the gas and the container walls.
12–68 Repeat Problem 12–67 by replacing CO2 by the
H2O gas.
12–69 A 2mdiameter spherical furnace contains a mixture
of CO2 and N2 gases at 1200 K and 1 atm. The mole fraction of
CO2 in the mixture is 0.15. If the furnace wall is black and its
temperature is to be maintained at 600 K, determine the net
rate of radiation heat transfer between the gas mixture and the
furnace walls.
12–70 A flowthrough combustion chamber consists of
15cm diameter long tubes immersed in water. Compressed air
is routed to the tube, and fuel is sprayed into the compressed
air. The combustion gases consist of 70 percent N2, 9 percent
H2O, 15 percent O2, and 6 percent CO2, and are maintained at
1 atm and 1500 K. The tube surfaces are near black, with an
emissivity of 0.9. If the tubes are to be maintained at a temperature of 600 K, determine the rate of heat transfer from combustion gases to tube wall by radiation per m length of tube.
12–71 Repeat Problem 12–70 for a total pressure of 3 atm. 12–72 In a cogeneration plant, combustion gases at 1 atm
and 800 K are used to preheat water by passing them through
6mlong 10cmdiameter tubes. The inner surface of the tube
is black, and the partial pressures of CO2 and H2O in combustion gases are 0.12 atm and 0.18 atm, respectively. If the tube
temperature is 500 K, determine the rate of radiation heat transfer from the gases to the tube.
12–73 A gas at 1200 K and 1 atm consists of 10 percent CO2,
10 percent H2O, 10 percent N2, and 70 percent N2 by volume.
The gas flows between two large parallel black plates maintained at 600 K. If the plates are 20 cm apart, determine the rate
of heat transfer from the gas to each plate per unit surface area. Special Topic: Heat Transfer from the Human Body
12–74C Consider a person who is resting or doing light
work. Is it fair to say that roughly onethird of the metabolic
heat generated in the body is dissipated to the environment by
convection, onethird by evaporation, and the remaining onethird by radiation?
12–75C What is sensible heat? How is the sensible heat loss
from a human body affected by (a) skin temperature, (b) environment temperature, and (c) air motion?
12–76C What is latent heat? How is the latent heat loss from
the human body affected by (a) skin wettedness and (b) relative humidity of the environment? How is the rate of evaporation from the body related to the rate of latent heat loss? 12–77C How is the insulating effect of clothing expressed?
How does clothing affect heat loss from the body by convection, radiation, and evaporation? How does clothing affect heat
gain from the sun?
12–78C Explain all the different mechanisms of heat transfer
from the human body (a) through the skin and (b) through
the lungs.
12–79C What is operative temperature? How is it related to
the mean ambient and radiant temperatures? How does it differ
from effective temperature?
12–80 The convection heat transfer coefficient for a clothed
person while walking in still air at a velocity of 0.5 to 2 m/s is
given by h 8.6 0.53, where is in m/s and h is in W/m2 · °C.
Plot the convection coefficient against the walking velocity,
and compare the convection coefficients in that range to the
average radiation coefficient of about 5 W/m2 · °C.
12–81 A clothed or unclothed person feels comfortable when
the skin temperature is about 33°C. Consider an average man
wearing summer clothes whose thermal resistance is 0.7 clo.
The man feels very comfortable while standing in a room
maintained at 20°C. If this man were to stand in that room unclothed, determine the temperature at which the room must be
maintained for him to feel thermally comfortable. Assume the
latent heat loss from the person to remain the same.
Answer: 26.4°C 12–82E An average person produces 0.50 lbm of moisture
while taking a shower and 0.12 lbm while bathing in a tub.
Consider a family of four who shower once a day in a bathroom that is not ventilated. Taking the heat of vaporization
of water to be 1050 Btu/lbm, determine the contribution of
showers to the latent heat load of the air conditioner in summer
per day.
12–83 An average (1.82 kg or 4.0 lbm) chicken has a basal
metabolic rate of 5.47 W and an average metabolic rate of
10.2 W (3.78 W sensible and 6.42 W latent) during normal activity. If there are 100 chickens in a breeding room, determine
the rate of total heat generation and the rate of moisture production in the room. Take the heat of vaporization of water to
be 2430 kJ/kg.
12–84 Consider a large classroom with 150 students on a hot
summer day. All the lights with 4.0 kW of rated power are kept
on. The room has no external walls, and thus heat gain through
the walls and the roof is negligible. Chilled air is available at
15°C, and the temperature of the return air is not to exceed
25°C. Determine the required flow rate of air, in kg/s, that
Answer: 1.45 kg/s
needs to be supplied to the room.
12–85 A person feels very comfortable in his house in light
clothing when the thermostat is set at 22°C and the mean radiation temperature (the average temperature of the surrounding
surfaces) is also 22°C. During a cold day, the average mean
radiation temperature drops to 18°C. To what level must the cen58933_ch12.qxd 9/9/2002 9:49 AM Page 662 662
HEAT TRANSFER
Thermocouple
Tth = 850 K
22°C
ε = 0.6 Air 22°C Tw = 500 K FIGURE P12–88 h 0.6 and the convection heat transfer coefficient to be
60 W/m2 · °C, determine the actual temperature of air.
Answer: 1111 K FIGURE P12–85
indoor air temperature be raised to maintain the same level of
comfort in the same clothing?
12–86 Repeat Problem 12–85 for a mean radiation temperature of 12°C.
12–87 A car mechanic is working in a shop whose interior
space is not heated. Comfort for the mechanic is provided by
two radiant heaters that radiate heat at a total rate of 10 kJ/s.
About 5 percent of this heat strikes the mechanic directly. The
shop and its surfaces can be assumed to be at the ambient temperature, and the emissivity and absorptivity of the mechanic
can be taken to be 0.95 and the surface area to be 1.8 m2. The
mechanic is generating heat at a rate of 350 W, half of which is
latent, and is wearing medium clothing with a thermal resistance of 0.7 clo. Determine the lowest ambient temperature in
which the mechanic can work comfortably. Radiant
heater 12–89 A thermocouple shielded by aluminum foil of emissivity 0.15 is used to measure the temperature of hot gases
flowing in a duct whose walls are maintained at Tw 380 K.
The thermometer shows a temperature reading of Tth 530 K.
Assuming the emissivity of the thermocouple junction to
be
0.7 and the convection heat transfer coefficient to be
h 120 W/m2 · °C, determine the actual temperature of the
gas. What would the thermometer reading be if no radiation
shield was used?
12–90E Consider a sealed 8in.high electronic box whose
base dimensions are 12 in. 12 in. placed in a vacuum chamber. The emissivity of the outer surface of the box is 0.95. If the
electronic components in the box dissipate a total of 100 W of
power and the outer surface temperature of the box is not to exceed 130°F, determine the highest temperature at which the
surrounding surfaces must be kept if this box is to be cooled by
radiation alone. Assume the heat transfer from the bottom surAnswer: 43°F
face of the box to the stand to be negligible. 12 in. 12 in.
100 W
ε = 0.95
Ts = 130°F Electronic
box 8 in. Stand FIGURE P12–87
Review Problems
12–88 A thermocouple used to measure the temperature
of hot air flowing in a duct whose walls are maintained at
500 K shows a temperature reading of Tth
850 K.
Tw
Assuming the emissivity of the thermocouple junction to be FIGURE P12–90E
12–91 A 2minternaldiameter doublewalled spherical tank
is used to store iced water at 0°C. Each wall is 0.5 cm thick,
and the 1.5cmthick air space between the two walls of the
tank is evacuated in order to minimize heat transfer. The surfaces surrounding the evacuated space are polished so that each
surface has an emissivity of 0.15. The temperature of the outer cen58933_ch12.qxd 9/9/2002 9:49 AM Page 663 663
CHAPTER 12
0°C 20°C
ε = 0.15 Iced
water Vacuum 2m 1.5
cm
0.5 cm 0.5 cm FIGURE P12–91
wall of the tank is measured to be 20°C. Assuming the inner
wall of the steel tank to be at 0°C, determine (a) the rate of heat
transfer to the iced water in the tank and (b) the amount of ice
at 0°C that melts during a 24h period.
12–92 Two concentric spheres of diameters D1 15 cm and
D2 25 cm are separated by air at 1 atm pressure. The surface
temperatures of the two spheres enclosing the air are T1
275 K, respectively, and their emissivities
350 K and T2
are 0.5. Determine the rate of heat transfer from the inner
sphere to the outer sphere by (a) natural convection and
(b) radiation. Water is heated as it flows through the tube, and the annular
space between the aluminum and the glass tube is filled with
air at 0.5 atm pressure. The pump circulating the water fails
during a clear day, and the water temperature in the tube starts
rising. The aluminum tube absorbs solar radiation at a rate of
30 Btu/h per foot length, and the temperature of the ambient air
outside is 75°F. The emissivities of the tube and the glass cover
are 0.9. Taking the effective sky temperature to be 60°F, determine the temperature of the aluminum tube when thermal equilibrium is established (i.e., when the rate of heat loss from the
tube equals the amount of solar energy gained by the tube).
12–95 A vertical 2mhigh and 3mwide doublepane window consists of two sheets of glass separated by a 5cmthick
air gap. In order to reduce heat transfer through the window,
the air space between the two glasses is partially evacuated to
0.3 atm pressure. The emissivities of the glass surfaces are 0.9.
Taking the glass surface temperatures across the air gap to be
15°C and 5°C, determine the rate of heat transfer through the
window by natural convection and radiation. 2m 15°C
5°C 12–93 Consider a 1.5mhigh and 3mwide solar collector
that is tilted at an angle 20° from the horizontal. The distance
between the glass cover and the absorber plate is 3 cm, and the
back side of the absorber is heavily insulated. The absorber
plate and the glass cover are maintained at temperatures of
80°C and 32°C, respectively. The emissivity of the glass surface is 0.9 and that of the absorber plate is 0.8. Determine the
rate of heat loss from the absorber plate by natural convection
Answers: 750 W, 1289 W
and radiation. Glass
1.5 cm Frame FIGURE P12–95
12–96 Glass
cover Solar
radiation
32°C
80°C A simple solar collector is built by placing a
6cmdiameter clear plastic tube around a garden hose whose outer diameter is 2 cm. The hose is painted
black to maximize solar absorption, and some plastic rings
are used to keep the spacing between the hose and the clear
plastic cover constant. The emissivities of the hose surface and
the glass cover are 0.9, and the effective sky temperature is Absorber
plate
Air space
θ = 20° Tsky = 15°C Solar
radiation
25°C Insulation Clear plastic tube
40°C Water FIGURE P12–93
12–94E A solar collector consists of a horizontal
aluminum tube having an outer diameter of
2.5 in. enclosed in a concentric thin glass tube of diameter 5 in. Spacer
Garden hose FIGURE P12–96 cen58933_ch12.qxd 9/9/2002 9:49 AM Page 664 664
HEAT TRANSFER estimated to be 15°C. The temperature of the plastic tube is
measured to be 40°C, while the ambient air temperature is
25°C. Determine the rate of heat loss from the water in the
hose by natural convection and radiation per meter of its length
under steady conditions.
Answers: 5.2 W, 26.2 W 12–97 A solar collector consists of a horizontal copper tube
of outer diameter 5 cm enclosed in a concentric thin glass tube
of diameter 9 cm. Water is heated as it flows through the tube,
and the annular space between the copper and the glass tubes is
filled with air at 1 atm pressure. The emissivities of the tube
surface and the glass cover are 0.85 and 0.9, respectively. During a clear day, the temperatures of the tube surface and the
glass cover are measured to be 60°C and 40°C, respectively.
Determine the rate of heat loss from the collector by natural
convection and radiation per meter length of the tube.
12–98 A furnace is of cylindrical shape with a diameter of
1.2 m and a length of 1.2 m. The top surface has an emissivity
of 0.70 and is maintained at 500 K. The bottom surface has an
emissivity of 0.50 and is maintained at 650 K. The side surface
has an emissivity of 0.40. Heat is supplied from the base
surface at a net rate of 1400 W. Determine the temperature of
the side surface and the net rates of heat transfer between the
top and the bottom surfaces, and between the bottom and side
surfaces. 12–100 A thin aluminum sheet with an emissivity of 0.12 on
both sides is placed between two very large parallel plates
maintained at uniform temperatures of T1 750 K and T2
550 K. The emissivities of the plates are 1 0.8 and 2 0.9.
Determine the net rate of radiation heat transfer between the
two plates per unit surface area of the plates, and the temperature of the radiation shield in steady operation.
12–101 Two thin radiation shields with emissivities of 3
0.10 and 4 0.15 on both sides are placed between two very
large parallel plates, which are maintained at uniform temperatures T1 600 K and T2 300 K and have emissivities
0.6 and 2 0.7, respectively. Determine the net rates of
1
radiation heat transfer between the two plates with and without
the shields per unit surface area of the plates, and the temperatures of the radiation shields in steady operation. T1 = 600 K
ε1 = 0.6
ε3 = 0.10 T2 = 300 K
ε2 = 0.7 ε4 = 0.15 FIGURE P12–101
T1 = 500 K
ε1 = 0.70
r1 = 0.6 m h = 1.2 m
T3
ε3 = 0.40 T2 = 650 K
ε2 = 0.50
r2 = 0.6 m FIGURE P12–98
12–99 Consider a cubical furnace with a side length of 3 m.
The top surface is maintained at 700 K. The base surface has
an emissivity of 0.90 and is maintained at 950 K. The side surface is black and is maintained at 450 K. Heat is supplied from
the base surface at a rate of 340 kW. Determine the emissivity
of the top surface and the net rates of heat transfer between the
top and the bottom surfaces, and between the bottom and side
surfaces. 12–102 In a naturalgas fired boiler, combustion gases pass
through 6mlong 15cmdiameter tubes immersed in water at
1 atm pressure. The tube temperature is measured to be 105°C,
and the emissivity of the inner surfaces of the tubes is estimated to be 0.9. Combustion gases enter the tube at 1 atm and
1200 K at a mean velocity of 3 m/s. The mole fractions of CO2
and H2O in combustion gases are 8 percent and 16 percent, respectively. Assuming fully developed flow and using properties of air for combustion gases, determine (a) the rates of heat
transfer by convection and by radiation from the combustion
gases to the tube wall and (b) the rate of evaporation of water.
12–103 Repeat Problem 12–102 for a total pressure of 3 atm
for the combustion gases. Computer, Design, and Essay Problems
12–104 Consider an enclosure consisting of N diffuse and
gray surfaces. The emissivity and temperature of each surface
as well as all the view factors between the surfaces are specified. Write a program to determine the net rate of radiation heat
transfer for each surface.
12–105 Radiation shields are commonly used in the design
of superinsulations for use in space and cryogenic applications.
Write an essay on superinsulations and how they are used in
different applications. cen58933_ch12.qxd 9/9/2002 9:49 AM Page 665 665
CHAPTER 12 12–106 Thermal comfort in a house is strongly affected by
the socalled radiation effect, which is due to radiation heat
transfer between the person and surrounding surfaces. A person
feels much colder in the morning, for example, because of the lower surface temperature of the walls at that time, although
the thermostat setting of the house is fixed. Write an essay on
the radiation effect, how it affects human comfort, and how it
is accounted for in heating and airconditioning applications. cen58933_ch12.qxd 9/9/2002 9:49 AM Page 666 ...
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This note was uploaded on 01/28/2010 for the course HEAT ENG taught by Professor Ghaz during the Spring '10 term at University of Guelph.
 Spring '10
 Ghaz

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