Unformatted text preview: Massachusetts Institute of Technology
Department of Aeronautics and
Astronautics
Cambridge, MA 02139 16.03/16.04 Unified Engineering III, IV
Spring 2004 Time
Spent
(min) Problem Set 4
F11/F12
F13
Name: F14
Due Date: 3/2/04 M10
M11
M12
M13
Study
Time Announcements: The Materials Quiz on Friday (2/27 ) will be at 9am Spring 2004 Uniﬁed Engineering
Fluids Problems F11–F14 F11+12. Air is drawn at high speed out of a large reservoir through a duct of constant area
˙
A, which contains a radiator delivering a known Q to the ﬂow (in Watts). The heating and
friction of the duct walls are negligible.
.
Q
h o 1 � 1 p 1 V1 h o �o po h o 2 � 2 p 2 V2 The known ﬂow quantities are:
ho = ho1 reservoir total enthalpy
�o reservoir total density
po reservoir total pressure
p2 outlet pressure (drives the ﬂow)
The remaining six unknown quantities inside the duct are:
ho2 outlet total enthalpy
V1 inlet velo city
V2 outlet velo city
�1 inlet density
�2 outlet density
p1 inlet pressure
A total of six equations are needed to solve for the six unknowns. One of these equations is
the isentropic relation b etween the reservoir and station 1,
p1
=
po � ho1 − 1 V12
2
ho �� /(� −1) and two additional ones are the state equations at stations 1 and 2.
�−1
1
�1 ho1 − V12
2
�
� �−1
12
=
� 2 ho 2 − V 2
2
� p1 =
p2 � Write down the remaining three equations by constructing a suitable control volume and
applying the integral mass, momentum, energy equations. (Do not try to solve the six
equations — it gets very messy!) F13. You stick your hand out the window of a car traveling at 75 mph, palm into the
wind. The ambient air conditions are � = 1.2 kg/m3 , p = 105 Pa, T = 300K� . For air,
cp = 1004 J/kg K� . Determine the conditions on the stagnation point on your palm.
F14. An aircraft is ﬂying at speed V� , in an atmosphere with p� , and ��
.
a) What is the ﬂight Mach number M� ? Give in terms of the quantities above.
b) Determine the stagnation pressure po at the nose of the aicraft in two ways:
i) The exact full compressible equation.
ii) The incompressible Bernoulli equation, pretending � = �� is constant.
Plot po /p� versus M� for the two equations. Also plot the “Bernoulli error”
(po /p� )exact − (po /p� )Bernoulli
versus M�
. What would you judge to be a reasonable upper Mach limit on the validity of
the Bernoulli equation? Spring 2004 Uniﬁed Engineering
StrMat / Fluids Problem M10/Fxx Consider two wings with the same span b = 2 m , and average chord cavg = 0.25 m, but
diﬀerent taper ratios:
Constant chord (cr = 0.250 m, ct = 0.250 m, r = 1.0)
Straight taper (cr = 0.333 m, ct = 0.167 m, r = 0.5)
Constant airfoil thickness/chord ratio κ = 0.08 everywhere. Assume local loading q (y ) is proportional to chord c(y ). Total load on halfwing is F = 10 N (15 oz gross weight at 5 g’s). For each wing . . . a) Determine q (y ), S (y ), M (y ) b) Assuming load is carried by top and bottom sparcaps with separation equal to local h(y ) = κ c(y ), determine sparcap load ±P (y ). c) Assuming max p ermissible sparcap stress (1 ksi = 7 MPa for balsa), calculate minimum cap area A(y ). Assuming balsa density of � = 0.125 g/cm3 , estimate sparcap mass. d) Compute b eam curvature at wing center � = M (0)/EI (0), and esimate tip deﬂection � = w (b/2) assuming w �� (y ) = � is constant along span. Balsa modulus: E = 200 ksi = 1.36 GPa.
e) Discuss structural and aerodynamic merits of straight vs tapered wing. Plotting of the
various distributions is suggested to help with interpretation. c(y) b/2
A(y)
h(y)
c(y) y Unified Engineering Spring 2004 Problem M11
A solid steel shaft of length 3 m is required to transmit a torque of 200 kNm. The
maximum allowable shear stress that the steel can support, ty , is 200 MPa (shear yield
stress).
(a) If the shaft has a solid circular cross section, determine the minimum diameter of
the shaft to transmit the torque without yielding. (b) If the shaft is instead hollow with a ratio of external to internal diameter of 5/4,
what is now the required diameter of the shaft, what is the weight saving over
case (a)?.
(c) What is the ratio of (i) the angle of twist between the ends of the shafts and (ii)
the torsional stiffness in the two cases?. (d) What is the maximum extensional stress acting in the shaft in (b), in what
direction(s) does it act?. Problem M12
The diagram below shows a rigid bar, length L, pinned at one end, which is
initially held vertical. The bar is stabilized by the pair of linear springs, stiffness
k, orientated at the angle q to the vertical. Find the critical value of the load P
which will cause collapse of this assembly. Hint: Consider the equilibrium of
the bar at a small displacement from the equilibrium position shown. P
q
k q
k L Problem M13
In problem M1 you designed a truss, however you took no account of the possibility of buckling.
Redo the question, with the same set of materials. Reexamine your design strategy (including
materials selection). Assume that all the materials are available in the form of bars with a solid
circular crosssection.
Problem M1
This is question is designed to provide you with a chance to revise material we met last term,
and an opportunity to start thinking about structural design. You are asked to design
a minimum mass truss structure that will be attached at points A, and B, 1 m apart on
a horizontal floor in order to support a vertical load of 10 kN, without exceeding the
strength (assume that the tensile and compressive strengths are the same) of the bars,
at a distance 2 m above the floor and 1m to the right of the right hand support point
(B).. The truss will be made of constant crosssection members of whatever material
you choose to select. All of the bars will have the same crosssection. The following
materials are available for selection. Select a material, and then choose an
appropriate truss configuration and then estimate the mass of the truss, such that it
will meet the design requirement. Explain your thought processes at each step. Material Density, r,
(Mg/m3) Modulus, E, CTE, a, Price , p, Tensile Strength, (GPa) x 10 K ($/Mg) sf , (MPa) Mild Steel 7.9 203 12 300 220 Aluminum alloy (2000 series) 2.8 71 24 1500 350 Titanium alloy Ti6Al4V 4.5 120 9.0 8000 850 Carbon fiber composite* 1.5 70 3.0 100000 700 Wood (e.g spruce)* 0.6 12 4.0 300 30 Silicon Carbide (SiC) 3.0 410 4.0 50000 300 6 1 Note. Although the design objective is to minimize the mass of the structure, the credit for the
question will be based on demonstrating a logical approach to selecting a material and a truss
configuration, and then obtaining an estimate for the mass of the truss. Do not spend more than
an hour on this question, and do not analyze multiple truss configurations. A useful exercise is
to estimate what you think the mass of the truss will be before you do any analysis  developing
an intuition for the correct size for structures is a useful skill to cultivate. ...
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Full Document
 Fall '05
 MarkDrela
 Fluid Dynamics, Force, Aeronautics, Astronautics, Truss, Stagnation pressure, Stagnation Point, stagnation pressure po

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