Question
A small rocket motor, fueled with hydrogen and oxygen, is tested on a thrust stand at a simulated altitude of 10 km. The motor is operated at chamber stagnation conditions of 1500 K and 8.0 MPa (gage). The combustion product is water vapor, which may be treated as an ideal gas. Expansion occurs through a converging-diverging nozzle with design Mach number of 3.5 and exit area of 700 mm². Find the pressure at the nozzle exit plane. Calculate the mass flow rate of exhaust gas. Determine the force exerted by the rocket motor on the thrust stand.
Answers
drwls
I have helped you with two of these nozzle flow problems already and would like to see you make an effort. I suggest you use isentropic flow tables and a specific heat ratio of 1.3 for water vapor, but you should confirm that. There is a formula for the thrust that involves the mass flow rate the exit velocity, as well as P(exit) and
P(ambient). You can get P(ambient) from the simulated altitude.
P(ambient). You can get P(ambient) from the simulated altitude.