Connect with LearnSmart for Anderson: Fundamentals of Aerodynamics, 6e
6th Edition
ISBN: 9781259683268
Author: Anderson, John
Publisher: Mcgraw-hill Higher Education (us)
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Chapter 3, Problem 3.10P
Prove that the velocity potential and the stream function for a uniform flow, Equations
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PROBLEM 10: A sleeve in the form of a circular tube of length L is Nut
placed around a bolt and fitted between washers at each end.
The nut is then turned until it is just snug.
Use material properties as follows:
For the sleeve, as = 21 x 106/°C and Es = 100 GPa
Washer
Bolt
·L·
Sleeve
Bolt head
For the bolt, αB = 10 × 10-6/°C and EB = 200 GPa.
1. Calculate the temperature rise that is required to produce a compressive stress of 25 MPa in the sleeve.
This problem illustrates that the factor of safety for a machine element depends on the particular point selected for
analysis. Here you are to compute factors of safety, based upon the distortion-energy theory, for stress elements at A and
B of the member shown in the figure. This bar is made of AISI 1006 cold-drawn steel and is loaded by the forces
F = 1.100 kN, P = 8.00 kN, and T = 50.00 N·m. Given: Sy = 280 MPa.
B
-100 mm-
15-mm D.
a) What is the value of the axial stress at point A?
b)What is the value of the shear stress at point A?
c)Determine the value of the Von Mises stress at
point A.
P
F
The three steel wires, each of cross-sectional area 0.05 in2, support the weight W. Theirunstressed lengths are 74.98 ft, 74.99 ft, and 75.00 ft. Use E = 29 x 106 psi.1. Find the stress (psi) in the longest wire if W = 1500 lb.2. Determine the stress in the shortest wire if W = 500 lb
ANSWERS: 6130 psi; 6930 psi
Chapter 3 Solutions
Connect with LearnSmart for Anderson: Fundamentals of Aerodynamics, 6e
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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