Loose Leaf for Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259683992
Author: Anderson, John
Publisher: McGraw-Hill Education
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Chapter 9, Problem 9.16P
Consider a circular cylinder (oriented with its axis perpendicular to the flow) and a symmetric diamond-wedge airfoil with a half-angle of
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8. All of the members in the Warren truss of Figure 8 are of length 10 ft. Use the method of
sections to determine the forces in the members BD,CD,CE.
B
A
C
D
E
F
G
2000 lb
3000 lb
5000 lb
Figure 8
H
An acrobat is walking on a tightrope of length L
=20.1 m attached to supports A and B at a
distance of 20.0 m apart. The combined weight
of the acrobat and his balancing pole is 900 N,
and the friction between his shoes and the rope
is large enough to prevent him from slipping.
Neglecting the weight of the rope and any
elastic deformation, determine the deflection (y)
and the tension in portion AC and BC of the
rope for values of x from 0.5 m to 10 m using
0.5 m increments.
1. Determine the maximum deflection (y) in
the rope.
2. Plot tension of AC and BC vs. x (on the
same plot with x on the x-axis). Turn in the
plot and the table of x, TAC, and TBC (clearly
label each).
A
C
20.0 m
B
5. A 4000 lb block of concrete is attached by light inextensible cables to the truss in Figure 5.
Determine the force in each member. State whether each member is in tension or compression.
3
ΘΑ
D
E
cables
all dimensions in feet.
Chapter 9 Solutions
Loose Leaf for Fundamentals of Aerodynamics
Ch. 9 - A slender missile is flying at Mach 1.5 at low...Ch. 9 - Consider an oblique shock wave with a wave angle...Ch. 9 - Equation (8.80) does not hold for an oblique shock...Ch. 9 - Consider an oblique shock wave with a wave angle...Ch. 9 - Consider the flow over a 22.2 half-angle wedge. If...Ch. 9 - Consider a flat plate at an angle of attack a to a...Ch. 9 - A 30.2 half-angle wedge is inserted into a...Ch. 9 - Consider a Mach 4 airflow at a pressure of 1 atm....Ch. 9 - Consider an oblique shock generated at a...Ch. 9 - Consider the supersonic flow over an expansion...
Ch. 9 - A supersonic flow at M1=1.58 and p1=1atm expands...Ch. 9 - A supersonic flow at M1=3,T1=285K, and p1=1atm is...Ch. 9 - Consider an infinitely thin flat plate at an angle...Ch. 9 - Consider a diamond-wedge airfoil such as shown in...Ch. 9 - Consider sonic flow. Calculate the maximum...Ch. 9 - Consider a circular cylinder (oriented with its...Ch. 9 - Consider the supersonic flow over a flat plate at...Ch. 9 - (The purpose of this problem is to calculate a...Ch. 9 - Repeat Problem 9.18, except with =30. Again, we...Ch. 9 - Consider a Mach 3 flow at 1 atm pressure initially...Ch. 9 - The purpose of this problem is to explain what...
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