PERFORMANCE SUMMARY OF THE SUPERSONIC DIFFUSER AND ITS APPLICATION TO ALTITUDE TESTING OF CAPTIVE ROCKET ENGINES
AIR FORCE FLIGHT TEST CENTER EDWARDS AFB CA
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The inal results are presented of a development program, initiated to determine the altitude simulation produced by various second and third stage rocket engines enclosed in an altitude chamber and fired into a constant cross-sectional area diffuser. The diffuser and supersonic nozzle configurations were tested utilizing nitrogen gas as the primary fluid and also with 1000 pound thrust solid propellant rocket engines. The experimental results are in accord with the one dimensional equations describing part of the diffuser performance curve and establish a criteria for comparison with the results obtained from the 1000 pound thrust solid propellant rockets. The resulting data presents a method of diffuser application for captive rocket engine testing at altitudes in excess of 100,000 feet. The minimum altitude chamber pressure produced with a solid propellant 15 degree conical Mach 4 configuration was .008 atmospheres while the minimum altitude chamber pressure produced in the nitrogen gas tests was .006 atmospheres with a slowly diverging Mach 4 configuration.
- Rocket Engines