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

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

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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