For a normal shock wave in air Mach number is 3.

If the atmospheric pressure and air density are $26.5~ KN/m^2 $ and $0.413 ~kg/m^3$ respectively, determine the flow Conditions before and after the shock wave. Take $\gamma = 1.4$

Solution:

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

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

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

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

Mach number, $M_{2}$ :

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