Influence of Storable Propellant Liquid Rocket Design Parameters on Combustion Instability.
Final technical rept. Jun 66-Nov 67,
AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA
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An experimental and analytical investigation has been conducted to establish correlation between thrust chamber design parameters and resultant combustion phenomena. The tests were made with self-impinging doublet injectors in a 15-in. -diameter pulse motor using Nitrogen tetroxide and monomethyl hydrazine. Pulse guns were used to disturb the combustion process and rate combustion stability. The analytical, vaporization-controlled, combustion models were used to compute the stability characteristics of the experimental thrust chamber at each operating condition. The stability model was then evaluated by comparing the hot-firing test results with the predicted stability characteristics. Author
- Liquid Propellant Rocket Engines
- Liquid Rocket Propellants