
Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Textbook Question
Chapter 3, Problem 3.6P
A Pilot tube on an airplane flying at standard sea level reads
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25 mm
10 mm
250 mm
a
15 mm
250 mm
0.3 m
(300 mm)
A
n
65 kN 90 kN 65 kN
B
PROBLEM 6.11
For the beam and loading shown,
consider section n-n and determine (a)
the largest shearing stress in that section,
(b) the shearing stress at point a.
15 mm
0.6 m
0.6 m
0.6 m 0.6 m
A
000
RA 1.8 m
P
W610 X 155
C
B
2.7 m-
RC
PROBLEM 6.17
For the wide-flange beam with the loading shown, determine the
largest load P that can be applied, knowing that the maximum
normal stress is 165 MPa and the largest shearing stress using the
approximation T = VIA web is 100 MPa.
PROBLEM 6.31
The built-up beam shown is made up by gluing together five
planks. Knowing that the allowable average shearing stress in the
glued joints is 400 kPa, determine the largest permissible vertical
shear in the beam.
50 mm
100 mm
50 mm
125 50 125
mm mm mm
Chapter 3 Solutions
Fundamentals of Aerodynamics
Ch. 3 - For an irrotational flow. show that Bernoullis...Ch. 3 - Consider a venturi with a throat-to-inlet area...Ch. 3 - Consider a venturi with a small hole drilled in...Ch. 3 - Consider a low-speed open-circuit subsonic wind...Ch. 3 - Assume that a Pitot tube is inserted into the...Ch. 3 - A Pilot tube on an airplane flying at standard sea...Ch. 3 - At a given point on the surface of the wing of the...Ch. 3 - Consider a uniform flow with velocity V. Show that...Ch. 3 - Show that a source flow is a physically possible...Ch. 3 - Prove that the velocity potential and the stream...
Ch. 3 - Prove that the velocity potential and the stream...Ch. 3 - Consider the flow over a semi-infinite body as...Ch. 3 - Derive Equation (3.81). Hint: Make use of the...Ch. 3 - Derive the velocity potential for a doublet; that...Ch. 3 - Consider the nonlifting flow over a circular...Ch. 3 - Consider the nonlifting flow over a circular...Ch. 3 - Consider the lifting flow over a circular cylinder...Ch. 3 - The lift on a spinning circular cylinder in a...Ch. 3 - A typical World War I biplane fighter (such as the...Ch. 3 - The Kutta-Joukowski theorem, Equation (3.140), was...Ch. 3 - Consider the streamlines over a circular cylinder...Ch. 3 - Consider the flow field over a circular cylinder...Ch. 3 - Prove that the flow field specified in Example 2.1...
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