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Unformatted text preview: Massachusetts Institute of Technology
Department of Aeronautics and
Astronautics
Cambridge, MA 02139 16.01/16.02 Unified Engineering I, II
Fall 2003 Problem Set 15 Time Spent
(min)
F21 Name: F22
M23
Due Date: Not Due M24
M25
Study
Time Announcements: Good luck on your finals. Reminder: The unified final is on Monday,
12/15 at 9am Fall 2003 Uniﬁed Engineering
Fluids Problems F21–F22 F21. As shown in class, the nonlifting irrotational ﬂow past a circular cylinder can be
represented by superimposing the uniform freestream ﬂow and a doublet. An alternative
representation is proposed using a source sheet placed on the cylinder surface as shown. The
proposed sheet strength distribution about the cylinder is �(� ) = −2V� cos � . There is no
vortex sheet, so on the surface, � = 0. �(�) freestream+doublet
model
(known) actual � freestream + source sheet
model
(proposed) You are to determine whether the new model is correct.
a) Determine the velocity at p oint A from the known exterior surface velocities for the
cylinder.
V� (� ) = −2V� sin �
,
Vr = 0
Using the sheet jump relations,
�Vn = � , �Vs = � determine the interior velocity at p oint B.
b) Again using the known exterior V� (� ), Vr result at point C, use the sheet jump condition
to determine the velocity at p oint D.
c) Compare velocities at B and D. What appears to be the ﬁctitious velocity inside the
cylinder?
d) Is the source sheet jump �Vn = � consistent with the exterior and interior normal ﬂows
everywhere on the cylinder surface? Is the proposed sourcesheet model correct?
C
D
A B ? F22. A long rectangular wing has span b and chord c, and hence the wing area is S = bc.
a) The wing airfoil has certain lift and drag coeﬃcients c� and cd which are constant across
the span. Determine how these relate to the wing’s overall CL and CD .
(Hint: Determine L and D , then get L and D , then from these determine CL and CD ).
The wing airfoil has a drag p olar which can be approximated by
cd � 0.01 + 0.015 c3
�
in the range c� = 0.1 . . . 1.2. The propulsive power P needed to overcome drag D at ﬂight
speed V� is given by
P = D V� P cl
1.0 ? 0.5 0.0 0.01 0.02 cd V b) Determine the form of the P (V� ) relation in level ﬂight, and plot it for the range c� =
0.1 . . . 1.2. Any constant multiplicative factors on the P and V� axes are not important –
only the shape of the curve is of interest. Hint: Simplest approach is to plot P (c� ) versus
V (c� ) with c� as a dummy parameter.
(Note: Using only the airfoil’s cd ignores other contributions such as induced drag, which
b ecome especially signiﬁcant at low ﬂight speeds!) Unified Engineering Fall 2003 Problem M23 (Materials and Structures)
The potential energy, U of a pair of atoms in a solid can be written as:
A B
U= m + n
r
r
where r is the separation of the atoms and A, B, m and n are positive constants. Indicate the
physical significance of the two terms in this equation.
A material has a simple cubic unit cell with atoms placed at the corners of the cubes. Show
that, when the material is stretched in a direction parallel to one of the cube edges, Young's
modulus E is given by:
E= mnkTM
W Where W is the mean atomic volume, k is Boltzmann's constant and TM is the absolute melting
temperature of the solid. You may assume that U0 ( r0 ) =  kTM ,where r0 is the equilibrium
separation of a pair of atoms. Problem M24
Two metals of current and historical interest for aerospace applications, nickel and
magnesium, have face centered cubic and close packed hexagonal structures respectively.
a) Assuming that the atoms can be represented as hard spheres, calculate the percentage of
the volume occupied by atoms in each material.
b) Calculate, from first principles, the dimensions of the unit cell in nickel and in magnesium.
(The densities of nickel and magnesium are 8.90 Mgm3 and 1.74 Mgm3 respectively, the
atomic weight of Nickel is 58.69, Magnesium is 24.31, Avogadro’s number is 6.023x1023). Problem M25
In addition to chapters 47 of Ashby and Jones Engineering Materials, you may also find
the chapters on polymers in Ashby and Jones, Engineering Materials 2, helpful (this is a
green covered book, available in the AeroAstro library).
a) Define the term polymer and list three engineering polymers. b) Define a thermoplastic and a thermoset. c) Distinguish between a crosslinked and a noncrosslinked polymer. d) What is the glass transition temperature? e) Explain the change in moduli of polymers at the glass transition temperature. f) What is the range of temperature in which TG lies for most engineering polymers? g) How would you increase the modulus of a polymer? ...
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 Fall '05
 MarkDrela
 Aeronautics, Astronautics

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