Fundamentals of Aerodynamics
Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 1, Problem 1.3P

Consider an infinitely thin flat plate of chord c at an angle of attack α in a supersonic flow. The pressures on the upper and lower surfaces are different but constant over each surface; that is, p u ( s ) = c 1 and p l ( s ) = c 2 , where c 1 and c 2 are constants and c 2 > c 1 . Ignoring the shear stress, calculate the location of the center of pressure.

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