PARAMETRIC STUDY OF ROCKET INSTABILITY.
Abstract
Research was conducted to determine those dimensionless parameters that may be employed as criteria for predicting the stability of combustion in a thrust chamber. UNMIXED GASEOUS PROPELLANTS: Unmixed propellants with impinging jet injectors yield combustion pressure oscillation similar to that obtained for premixed propellants with respect to fuel reactivity. BIPHASE PROPELLANTS (LIQUID FUEL-GASEOUS OXIDIZER): Investigations were conducted to determine the effects of (1) both the air and propellant injection velocities, chamber pressure, and fuel-air ratio on the steady-state operating characteristics of a rocket motor, and (2) selected parameters on propellant vaporization rate. CORRELATION OF RESULTS WITH SIMILARITY VARIABLES: Dimensionless parameters were derived that are sensitive to the occurrence of small amplitude pressure oscillations in the burning gaseous medium in a cylindrical combustion chamber. THEORETICAL ANALYSIS: An analysis was completed of the longitudinal combustion pressure oscillations for one model of the combustion zone.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 17, 1965
- Accession Number
- AD0614657
Entities
People
- M. J. Zucrow
Organizations
- Purdue University