Problem-4: A nozzle is to be designed for a supersonic helium supersonic wind tunnel. Test section (see Figure) specifications are as flow: Diameter 10 cm, Mach number = 3, Static pressure = 12.1 kPa and Static temperature = 217 K. Assume isentropic flow in the nozzle at the design condition Assume that helium behaves as a perfect gas, with y = 1.667 (constant) and R = 2077 J/Kg K. (a) Calculate the mass flow that must be provided. (b) Also, calculate the nozzle throat area and the reservoir temperature and pressure. Test Section Preservoir Preservo Treservoir Test Section Fgure 7.7 Problem-5: A converging-diverging nozzle with an area ratio (exit area/throat area) of 3.0 exhausts into a reservoir where the pressure is 1 atm. The nozzle is supplied by air at 22°C from a large chamber. At what pressure should the air in the chamber be for the nozzle to operate at its design condition? What will the outlet velocity be?