calculate (a) the pressure coefficient at the stagnation point

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1. Consider a laminar boundary layer on a fiat plate. At the trailing edge of the plate, with a free-stream Mach number of 2, the boundary layer thickness is 0.3 in. Assuming that the Reynolds number is held constant, calculate the boundary layer thickness for a Mach number of20. 2. Consider a hypersonic vehicle flying at Mach 20 at a standard altitude of 59 km. Calculate the air temperature at a stagnation point on this vehicle. Comment on the accuracy of your answer. 3. Assume that the nose of the Space Shuttle is spherical, with a nose radius of 1 ft. At Mach 18, calculate (a) the pressure coefficient at the stagnation point and (b) the pressure coefficient at a distance of 6 in away from the stagnation point measured along the surface.


 

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