INTERNAL ENVIRONMENT OF SOLID ROCKET NOZZLES
Abstract
Solid propellant nozzle environment was studied to implement nozzle design methods. Study of the condensed phase effects is emphasized. Cold flow modeling technique has been developed to the point of showing quantitative particle impingement rates for the 60-in. diameter engine modeled. Engine firing tests have provided the first data on heat fluxes to a molybdenum nozzle wall showing the effects of impinging alumina. A scanning spectrometer system has been completed for use in analyzing the alumina cloud emissivity. This is especially important in radiation calculations for large engines.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 30, 1964
- Accession Number
- AD0434129
Entities
People
- F. C. Price
- R. A. Dupuis
- V. A. Marple