Supersonic Combustion of Liquid Kerosene.
Abstract
This study first considers the cycle performance of scramjet engines up to Mach 14 including mixing losses. It was shown that optimum combustion efficiencies lie in the range 70 to 90%. Experimental and theoretical studies of kerosene injection and combustion in a supersonic airstream to 6000K were carried out. A combustion driven tailored interface shock tunnel was used for the experimental work with pressure and optical instrumentation. Satisfactory agreement was obtained between theory and experiment.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1975
- Accession Number
- ADA013137
Entities
People
- Roy Payne
Organizations
- University of Sheffield