Question

SOLVE QUESTION NUMBER 2 ONLY

1). A rocket nozzle produces 1 MN of thrust at sea level (ambient pressure and temperature 100 kPa and 300 K). The stagnation pressure and temperature are 5 MPa and 2800 K. Determine (a) the exit to throat area ratio (b) exit Mach number (c) exit velocity (d) mass flow rate and (e) exit area. Determine the thrust developed by the nozzle at an altitude of 20 km, where the ambient pressure and temperature are 5.46 kPa and 217 K. Assume the working fluid to be air with γ = 1.4. [5.12; 3.2; 1944 m/s; 514.4 kg/s; 0.6975 m2 ; 1.066 MN]

2). Assume that the rocket nozzle of the previous problem is designed to develop a thrust of 1 MN at an altitude of 10 km. Determine the thrust developed by the nozzle at 20 km, for the same stagnation conditions in the thrust chamber. Take the ambient pressure and temperature at 10 km to be 26.15 kPa and 223 K. Do you expect to see a normal shock in the nozzle divergent portion during sea level operation? [1.033 MN]

SOLVE QUESTION NUMBER 2 ONLY

Answer 1