Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 9, Problem 9.10P
Consider the supersonic flow over an expansion corner, such as given in Figure 9.25. The deflection angle
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11-68. The rectangular plate shown is subjected to a uniaxial
stress of 2000 psi. Compute the shear stress and the tensile
developed on a plane forming an angle of 30° with the longitud
axis of the member. (Hint: Assume a cross-sectional area of unity)
2000 psi
2000 psi
hp
11-70. A shear stress (pure shear) of 5000 psi exists on an element.
(a) Determine the maximum tensile and compressive stresses
caused in the element due to this shear.
(b) Sketch the element showing the planes on which the
maximum tensile and compressive stresses act.
11-20. An aluminum specimen of circular cross section, 0.50 in.
in diameter, ruptured under a tensile load of 12,000 lb. The plane
of failure was found to be at 48° with a plane perpendicular to the
longitudinal axis of the specimen.
(a) Compute the shear stress on the failure plane.
(b) Compute the maximum tensile stress.
(c) Compute the tensile stress on the failure plane.
hp
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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