Question

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.

Answer 1

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

Mach number, M₁ = 2 

Atmospheric pressure, p₁ = 26.5 kN/m² 

Air density, ρ₁ = 0.413 kg/m³

Mach number, M₂ :

Pressure, p₂ :

Density, ρ₂ :

Temperature, T₁ :