Atmospheric air flows through the converging diverging nozzle into a vacuum tank. The pressure inside the...

 

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Atmospheric air flows through the converging diverging nozzle into a vacuum tank. The pressure inside the tank is reduced to a magnitude to create a flow with an exit Mach number of 2.0 (refer to the Fig. 1). The tank is evacuated by closing the control valve until it satisfies the given condition. When the valve is opened, atmospheric air will start to flow through the converging-diverging nozzle into the tank. i. ii. iv. V. atmosphere Pam 101 kPa (abs) Tamu = 296 K Calculate the design exit area. throat 17=6.5 cm Figure 1 exit volume = 8.5 m² initial mass=0.45 kg initial temp = 296 K Determine the initial mass flow rate through the nozzle. Determine the tank pressure at which a normal shock wave will stand in the nozzle exit plane. Determine the exit Mach number when the shock is in the nozzle at a point where the cross-sectional area is 15% greater than the throat area. Determine the time until the flow in the nozzle becomes entirely subsonic. Atmospheric air flows through the converging diverging nozzle into a vacuum tank. The pressure inside the tank is reduced to a magnitude to create a flow with an exit Mach number of 2.0 (refer to the Fig. 1). The tank is evacuated by closing the control valve until it satisfies the given condition. When the valve is opened, atmospheric air will start to flow through the converging-diverging nozzle into the tank. i. ii. iv. V. atmosphere Pam 101 kPa (abs) Tamu = 296 K Calculate the design exit area. throat 17=6.5 cm Figure 1 exit volume = 8.5 m² initial mass=0.45 kg initial temp = 296 K Determine the initial mass flow rate through the nozzle. Determine the tank pressure at which a normal shock wave will stand in the nozzle exit plane. Determine the exit Mach number when the shock is in the nozzle at a point where the cross-sectional area is 15% greater than the throat area. Determine the time until the flow in the nozzle becomes entirely subsonic.