Determine the difference between these values and the

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An airplane flying at m0 = 0.8 under standard sea level conditions has instrumentation embedded at the stagnation point on its nose. Assuming that the flow brought to rest at this point has undergone an isentropic process, calculate the temperature and pressure there. Determine the difference between these values and the corresponding static values in the undisturbed atmosphere ahead of the airplane.

Reference no: EM13625630

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