Accession Number:

AD0851087

Title:

Influence of Storable Propellant Liquid Rocket Design Parameters on Combustion Instability.

Descriptive Note:

Final technical rept. Jun 66-Nov 67,

Corporate Author:

AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA

Report Date:

1969-01-01

Pagination or Media Count:

83.0

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

Subject Categories:

  • Liquid Propellant Rocket Engines
  • Liquid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE