Influence of Storable Propellant Liquid Rocket Design Parameters on Combustion Instability.
Abstract
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1969
- Accession Number
- AD0851087
Entities
People
- C. J. Abee
- C. W. Mclaughlin
- R. R. Weiss
Organizations
- Air Force Research Laboratory