Unformatted text preview: is 0.15. The nozzle discharges to the atmosphere; the discharge area is 0.015 m 2 . Determine the magnitude and direction of the force that must be applied to hold the nozzle in place. 4. 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 8.5 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 mm 2 . Evaluate 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....
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- Fall '08
- Fluid Dynamics, Mach number, Mass flow rate