Consider the supersonic flow over an expansion corner, such as given in Fig. 9.20. The deflection angle

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Consider the supersonic flow over an expansion corner, such as given in Fig. 9.20. The deflection angle θ = 23.38°. If the flow upstream of the corner is given by M1 = 2, P1 = 0.7atm, T1, = 630°R, calculate M2, p2, T2, p2, P0,2, and T0,2 downstream of the corner. Also, obtain the angles the forward and rearward Mach lines make with respect to the upstream direction.

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Managerial Accounting For Undergraduates

ISBN: 9780357499948

2nd Edition

Authors: James Wallace, Scott Hobson, Theodore Christensen

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