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 convergingdiverging 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....
View
Full Document
 Fall '08
 SCHOBEIRI
 Fluid Dynamics, Mach number, Mass flow rate

Click to edit the document details