Just upstream of a normal shock in an airflow ma 30 t 600

Question

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.