(b) Air, at an absolute pressure of 5 atm and a temperature of 15C, is drawn...

  

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(b) Air, at an absolute pressure of 5 atm and a temperature of 15°C, is drawn from a large plenum through a converging-diverging nozzle. The nozzle throat diameter is 6.35 mm and diverging section exit diameter is 7.15 mm. (i) Using the area-Mach number relationship determine the design Mach number for this nozzle. (ii) By applying the continuity equation at the throat determine the mass flow rate through the nozzle at the design condition. (iii) When a normal shock stands in the exit plane of the nozzle, determine both the back-pressure and the Mach number just downstream of the exit. (b) Air, at an absolute pressure of 5 atm and a temperature of 15°C, is drawn from a large plenum through a converging-diverging nozzle. The nozzle throat diameter is 6.35 mm and diverging section exit diameter is 7.15 mm. (i) Using the area-Mach number relationship determine the design Mach number for this nozzle. (ii) By applying the continuity equation at the throat determine the mass flow rate through the nozzle at the design condition. (iii) When a normal shock stands in the exit plane of the nozzle, determine both the back-pressure and the Mach number just downstream of the exit.

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KA 14 k14 for air Pressure salio P286 from the table of 1Dimensional of i... View the full answer