Q4. A converging-diverging nozzle draws air from a large reservoir where the pressure and temperature are...

 

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Q4. A converging-diverging nozzle draws air from a large reservoir where the pressure and temperature are 400 kPa and 300 K respectively. The design Mach number is equal to 3.0 and the design mass flow rate is 10 kg/s. (a) When the nozzle is running at the design condition calculate in the exit plane (i) the static temperature, (ii) the static pressure, (iii) the velocity, and (iv) the area. (b) When the nozzle is running off design a shock wave is standing just at the exit of the nozzle. Calculate (i) the static pressure downstream of the shock, (ii) the Mach number downstream of the shock, and (iii) the stagnation pressure drop across the shock. Q4. A converging-diverging nozzle draws air from a large reservoir where the pressure and temperature are 400 kPa and 300 K respectively. The design Mach number is equal to 3.0 and the design mass flow rate is 10 kg/s. (a) When the nozzle is running at the design condition calculate in the exit plane (i) the static temperature, (ii) the static pressure, (iii) the velocity, and (iv) the area. (b) When the nozzle is running off design a shock wave is standing just at the exit of the nozzle. Calculate (i) the static pressure downstream of the shock, (ii) the Mach number downstream of the shock, and (iii) the stagnation pressure drop across the shock.

Answer rating: 100% (QA)

4 Hese all the o woed sepresents used Given P 400 When the nozzle is re running calcu... View the full answer