Consider the supersonic flow over an expansion corner, such as given in Fig 9 20 The deflection angle 23 38 If the flow upstream of the corner is given by M 1 2, P 1 0 7atm, T 1 , 630R, calculate M 2 , p 2 , T 2 , p 2 , P 0,2 , and T 0,2 downstream of the corner Also, obtain the angles the forward and rearward Mach lines make with respect to the upstream direction

Question: Consider the supersonic flow over an expansion corner, such as given in Fig. 9.20. The deflection angle = 23.38. If the flow upstream of

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, P_0,2, and T_0,2 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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