PERFORMANCE SUMMARY OF THE SUPERSONIC DIFFUSER AND ITS APPLICATION TO ALTITUDE TESTING OF CAPTIVE ROCKET ENGINES
Abstract
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1961
- Accession Number
- AD0256347
Entities
People
- Richard H. Mickola
Organizations
- Air Force Test Center