For a normal shock wave in air Mach number is 2. If the atmospheric pressure and air density are 26.5 kN/m2 and 0.413 kg/m3 respectively, determine the flow conditions before and after the shock wave. Take γ = 1.4.

Solution:

Let subscripts 1 and 2 represent the flow conditions before and after the shock wave.

Mach number, $ \quad M_{1}=2 \\ $

Atmospheric pressure, $ p_{1}=26.5 \mathrm{kN} / \mathrm{m}^{2} \\ $

Air density, $ \quad \rho_{1}=0.413 \mathrm{~kg} / \mathrm{m}^{3} \\ $

Mach number, $M_{2}$ :

$$ \begin{aligned} M_{2}^{2} &=\frac{(\gamma-1) …