Question: If t = 0 . 0 7 5 c determine the pressure on each surface of the supersonic airfoil illustrated in the sketch if the

If t =0.075 c determine the pressure on each surface of the supersonic airfoil illustrated in the sketch if the freestream Mach number is 2. The freestream pressure is 50 kPa. Note: Lift and drag are not required.
If t = 0 . 0 7 5 c determine the pressure on each

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