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Pressure coefficient and stagnation temperature 0.0/2.0 points (graded) An aircraft is cruising at a speed of M=0.77. The freestream temperature is 222.77 K, and rho=0.4097 kg/m³. The pressure is measured on a point along the wing, and it is found to be 9120 Pa. Calculate the Cp for this point. Assume isentropic flow. Calculate the stagnation temperature in Kelvin under these conditions. Assume isentropic flow.

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