1. Supersonic air in a wind tunnel at Mach 2.5 has a static pressure of 20.1 kPa and a

density of 0.5 kg/m³.

(a) Determine the air temperature in the wind tunnel.

(b) A blunt body in the test section of the wind tunnel creates a normal shock wave.

The ratio of the pressure downstream of the shock wave, P2, to the pressure

upstream of the shock wave, P₁, is 7.125. The ratio of downstream to upstream

densities is 3.333. Determine the temperature ratio, T2/T₁, across the normal

shock wave.