Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Textbook Question
Chapter 9, Problem 9.15P
Consider sonic flow. Calculate the maximum deflection angle through which this flow can be expanded via a centered expansion wave.
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Calculate the stress concentration factor (kt). the small diameter is 0.88 in and the bigger one is 2.64 in and the radius is 0.088 in. Moment is 240 lb - in, and torque is 1800 lb-in. Bending moment is 358.817 psi or 2.4739 Mpa and torsion due torque is 2691 .13 psi or 18.55 Mpa and Von Mises Stress is 32.2246 Mpa. Calculate the new stresses with the Kt value obtained. Use the table that is provide to obtained the KT value on is for bending and the other for tosion.
Calculate the stress concentration factor (kt). the small diameter is 0.88 in and the bigger one is 2.64 in and the radius is 0.088 in. Moment is 240 lb - in, and torque is 1800 lb-in. Bending moment is 358.817 psi or 2.4739 Mpa and torsion due torque is 2691 .13 psi or 18.55 Mpa and Von Mises Stress is 32.2246 Mpa. Calculate the new stresses with the Kt value obtained. Use the table that is provide to obtained the KT value.
Chapter 9 Solutions
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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