A converging-diverging air nozzle has a throat area of 0.1 m^2 and exit area of 0.2 m^2. The Mach number at the throat is 0.8. If the stagnation pressure is 100 kPa, the back pressure is a. 85 kPa: b. 60.8 kPa: c. 93 kPa: d. 40.3 kPa: e. 31.5 kPa It is desired to accelerate flow from M_1 = 0.30 at inlet section to M_2 = 0.80 at the exit section of the nozzle. The area ratio (inlet to exit) is: a. 2.05:
b. 3.0:
c. 1.5:
d. 6.0:
e. 1.95
In converging-diverging nozzle, the mass flow rate is 2 kg/sec. The exit area (A_g) and exit velocity are 0.1m^2 and 200m/sec. avec. The exit density is:
a. 0.1 kg/m^3:
b. 0.25 kg/m^3:
c. 1.3 kg/m^3:
d. 2.4 kg/m^3:
e. 5.8 kg/m^3
A converging-diverging nozzle has a throat area of 0.1127 m^2 and exit area of 0.2035 m^2. The stagnation pressure at inlet is 100 kPa. The back pressure is 98.3 kPa. The Mach number at the exit is:
a. 0.85:
b. 2.20:
c. 0.30:
d. 0.55:
e. 0.16
Combustion gases with K = 1.33 &converging nozzle at stagnation temperature and pressure of 400 degree C and 900 kPa, and are discharged into the atmosphere with back pressure of 100 kPa. The lowest pressure that will occur within the nozzle is:
a. 312 kPa:
b. 100kPa:
c. 321 kPa:
d. 486 kPa:
e. 672 kPa