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 p2 = 1.75×10* N/m². You can assume isentropic flow conditions. a) Calculate the total pressure po based on the freestream conditions. b) Calculate the corresponding local Mach number M2 at the aforementioned local point. c) Based on the value for this local Mach number as calculated in part b, what can you say about the freestream Mach number M, with respect to the critical Mach number M? p2 = 1.75×104 N/m² M2 = ? h = 10,000 m M, = 0.85

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I have three parts that I need answered pertaining to the print provided below.   What material is specified for this part? (Multiple Choice)a. Cold Drawn Steel CD1040b. Hot Rolled Steelc. Delrin #360d. Brass FM#360 What size paper was used for the original version of this print? (Multiple Choice)ABCD The two views near the bottom of the print are called detail views. Which one of theviews above (left side, front, or right side) shows the same geometry, but at the normal 1:1scale? (Multiple Choice)a. left sideb. frontc. right side

I need answers for problems 7, 8, and 9 pertaining to the print provided.