Answered: Consider a supersonic flow with M = 2,…

Consider a supersonic flow with M = 2, p = 1 atm, and T = 288 K. This flow isdeflected at a compression corner through 20◦. Calculate M, p, T , p0, and T0 behind the resulting oblique shock wave.

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)

8th Edition

ISBN:9781305387102

Author:Kreith, Frank; Manglik, Raj M.

Publisher:Kreith, Frank; Manglik, Raj M.

Chapter5: Analysis Of Convection Heat Transfer

Section: Chapter Questions

Problem 5.68P

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Consider a supersonic flow with M = 2, p = 1 atm, and T = 288 K. This flow is
deflected at a compression corner through 20^◦. Calculate M, p, T , p₀, and T₀ behind the resulting oblique shock wave.

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