3 Consider the supersonic flow over a 4 half-angle wedge at zero angle of attack. The freestream Mach number ahead of th

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3 Consider the supersonic flow over a 4 half-angle wedge at zero angle of attack. The freestream Mach number ahead of th

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3 Consider The Supersonic Flow Over A 4 Half Angle Wedge At Zero Angle Of Attack The Freestream Mach Number Ahead Of Th 1
3 Consider The Supersonic Flow Over A 4 Half Angle Wedge At Zero Angle Of Attack The Freestream Mach Number Ahead Of Th 1 (15.46 KiB) Viewed 43 times
3 Consider the supersonic flow over a 4 half-angle wedge at zero angle of attack. The freestream Mach number ahead of the wedge is 1.4 at standard sea level conditions. The pressures on the upper and lower surfaces of the wedge are constant with distances and equal to each other, namely, Pu = p = 1.21x105 N/m2. The pressure exerted on the base of the wedge is equal to poo, The chord length, c, of the wedge is 1 m. Calculate the drag force on the wedge due to pressure.
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