A supersonic wind tunnel is intended to test flight conditions in the lower stra

Question

A supersonic wind tunnel is intended to test flight conditions in the lower stratosphere (-50,000 ft), and therefore docs not have a heated reservoir. The reservoir currently is at 530 degree R. Compute the Mach number in the test section if the pressure and temperature there matches that of the standard atmosphere at 50,000 ft. Compute the pressure and density in the reservoir. Compute the cross-sectional area ratio between the throat and the test section. A square flat plate is placed in the test section at an angle of attack of 3 degree s. Compute the lift and wave drag coefficients for this flat plate. As the day grows warmer, the air in the reservoir becomes warmer as well. Would you expect this to increase or decrease the coefficient of lift measured for the flat plate?

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