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Unformatted text preview: chamber temperature is 3000K. The velocities in the combustion chamber are small. Assume the flow behaves as an ideal gas with c p = 1.5 kJ/kg-K, =1.2. Fuel Oxidizer Inlet Inlet Combustion Chamber Pump Nozzle Ox a) If the flow is adiabatic, what is the exit velocity when the rocket exhausts into standard atmospheric conditions? What are the static temperature and Mach number for this exit velocity? b) What would the exit velocity, static temperature and Mach number be if the flow were fully-expanded to p e = 0 in space? c) Assume that about 20% of the total enthalpy of the flow in the combustion chamber is lost due to heat transfer to the walls of the combustion chamber. Now what is the exit velocity at standard atmospheric conditions and in space? (Assume that the chamber pressure is the same whether or not there is heat transfer.) (LO# 4)...
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This note was uploaded on 01/28/2012 for the course AERO 16.01 taught by Professor Markdrela during the Fall '05 term at MIT.
- Fall '05