Consider an infinitely thin flat plate of chord c at an angle of attack α in a supersonic flow. The pressure on the upper and lower surfaces are different but constant over each surface; that is, pu(s) = C1 and pl(s) = C2, where C1 and C2 are constants and C2 > C1. Ignoring the shear stress, calculate the location of the center of pressure.

X_cp = c/2

Explanation:

We are given;

Chord = c

Angle of attack = α

p u (s) = c 1

p1(s)=c2,

and c2 > c1

First of all, we need to find the resultant normal force on the plate and the total moment about leading edge.

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answer:

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explanation:

answer:

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