Air approaches a normal shock at (V_{1}=900 mathrm{~m} / mathrm{s}, p_{1}=50 mathrm{kPa}) absolute, and (T_{1}=220 mathrm{~K}). What

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Air approaches a normal shock at \(V_{1}=900 \mathrm{~m} / \mathrm{s}, p_{1}=50 \mathrm{kPa}\) absolute, and \(T_{1}=220 \mathrm{~K}\). What are the velocity and pressure after the shock? What would the velocity and pressure be if the flow were decelerated isentropically to the same Mach number?

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Ali Khawaja

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