ABLATION OF EXTREME-TEMPERATURE-RESISTING MATERIALS IN ROCKET EXHAUSTS
Abstract
The ablation rate of contoured Micarta (laminated plastics) specimens immersed in solid propellant exhaust gases was measured under closely controlled conditions. The effect of particles in the exhaust stream was demonstrated by carrying out firings with propellants containing 0.5%, 8%, and 16% aluminum. Firings at chamber pressures of 400 psia and 550 psia showed the effect of pressure on ablation rate. The ablation rate increased directly with chamber pressure and aluminum content of the propellant. Raw data for heating rate calculations were obtained for each propellant from instrumented copper calorimeters and heat flux transducers.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 09, 1965
- Accession Number
- AD0473835
Entities
People
- Joe M. Viles