For a given Prandtl-Meyer expansion, the upstream Mach number is 3 and the pressure ratio across the wave is p,/p, = 0.4. Calculate the angles of the forward and rearward Mach lines of the expansion fan relative to the free-stream direction.

A normal shock occurs in a stream of oxygen. The oxygen flows at Ma=1.8 and the upstream pressure and temperature are 40 psia and 85 degrees Fahrenheit. a) Calculate the following on the downstream side of the shock: static pressure, stagnation pressure, static temperature, stagnation temperature, static density, and velocity. b)If the Mach number is doubled to 3.6, what will be the resulting values of the parameters listed in part (a)?

Air flows isentropically through a duct as shown in the figure below. For the conditions shown, find the Mach number at both stations 1 and 2 and the flowrate. The diameter is not necessarily constant. Ma₁ (1) D₁ = 0.15 m V₁ = 40 m/s P1 = 4 atm abs. Ma₁ = Ma₂ = i m₁ = M. kg/s Ma₂ (2 T₂ = 225 K P2 = 2 atm abs.