Question 7 - Supersonic Wind Tunnel (15 points): A blow down supersonic wind tunnel has a test section area of 0.2 m and a design Mach number of 2.5. The pressure and temperature in the high pressure air tank is 50 MPa and 400 K. Ignore all losses between the high pressure tank and the test section. Supersonic nozzle Settling chamber Pressure control High-pressure tank Sonic throat. Test section Model Support Spreader Screens a) Estimate the throat area of the nozzle. b) Estimate the static pressure and static temperature in the test section. c) Estimate the required gas temperature in the high pressure tank to achieve 298 K temperature in the test section. Exit throat Exit