Consider the air flow over the wing of a civil airliner flying at M. 0.85 and at an altitude of 10,000 m. At some local point above the wing, the local static pressure reduces to 1.75×10ª N/m². You...

Please circle or box final answer. Show which part the work is under

Extracted text: Consider the air flow over the wing of a civil airliner flying at M. 0.85 and at an altitude of 10,000 m. At some local point above the wing, the local static pressure reduces to 1.75×10ª N/m². You can assume isentropic flow conditions. a) Calculate the corresponding local Mach number at this specific point. b) Based on the value for this local Mach number as calculated in part a, what can you say about the freestream Mach number M, with respect to the critical Mach number Mer?