Loose Leaf for Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259683992
Author: Anderson, John
Publisher: McGraw-Hill Education
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Textbook Question
Chapter 8, Problem 8.13P
Repeat Problems 8.11 and 8.12 using (incorrectly) Bernoulli’s equation for incompressible flow. Calculate the percent error induced by using Bernoulli’s equation.
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Draw top, side, front view With pen(cil) and paper
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A wheel of diameter 150.0 mm and width 37.00 mm carrying a load 2.200 kN rolls on a
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figure given, which is based on a Poisson's ratio of 0.3, is applicable to estimate
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depth, calculate the Hertzian stresses σr, σy, σz, and Tmax for the wheel.
1.0
0.8
0, т
Ratio of stress to Pmax
0.4
0.6
90
69
0.2
0.5b
b
1.5b
Tmax
2b
Distance from contact surface
The Hertizian stresses are as follows:
02 = or = -23.8 psi for the wheel =|
necessary.)
σy for the wheel =|
MPa
σz for the wheel =
MPa
V4 for the wheel = |
MPa
2.5b
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Only question 3
Chapter 8 Solutions
Loose Leaf for Fundamentals of Aerodynamics
Ch. 8 - Consider air at a temperature of 230 K. Calculate...Ch. 8 - The temperature in the reservoir of a supersonic...Ch. 8 - At a given point in a flow, T=300K,p=1.2atm, and...Ch. 8 - At a given point in a flow, T=700R,p=1.6atm, and...Ch. 8 - Consider the isentropic flow through a supersonic...Ch. 8 - Consider the isentropic flow over an airfoil. The...Ch. 8 - The flow just upstream of a normal shock wave is...Ch. 8 - The pressure upstream of a normal shock wave is 1...Ch. 8 - The entropy increase across a normal shock wave is...Ch. 8 - The how just upstream of a normal shock wave is...
Ch. 8 - Consider a flow with a pressure and temperature of...Ch. 8 - Consider a flow with a pressure and temperature of...Ch. 8 - Repeat Problems 8.11 and 8.12 using (incorrectly)...Ch. 8 - Derive the Rayleigh Pitot tube formula, Equation...Ch. 8 - On March 16, 1990, an Air Force SR-71 set a new...Ch. 8 - In the test section of a supersonic wind tunnel, a...Ch. 8 - When the Apollo command module returned to earth...Ch. 8 - The stagnation temperature on the Apollo vehicle...Ch. 8 - Prove that the total pressure is constant...
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