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2 3 Throat -- Consider air flowing through the supersonic wind tunnel shown in the figure. The tunnel has a throat area of 0.07 m. The density and temperature of the flow at the throat are 0.1 kg/m and 320K. Ignore dissipative effects, except in the shock. No heat is added. The flow at location 1 is subsonic. Determine: a. The mass flow rate through the wind tunnel. b. The Mach number at location 2 is measured to be 3.20. Estimate the cross sectional area of the tunnel at this location. C. The temperature of the flow measured at location 3 is 368K. Estimate the Mach number of the flow here