Estimate the mach number of the flow entering the shock

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1. The stagnation pressure ratio across a normal shock in an airflow is 0.6. Estimate the Mach number of the flow entering the shock.

2. Just upstream of a normal shock in an airflow, Ma = 3.0, T = 600 °R, and p = 30 psia. Estimate values of Ma, T0, T, p0, p, and V downstream of the shock.

Reference no: EM131369117

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