STUDIES OF HYDROGEN-AIR SUPERSONIC COMBUSTION AT LOW DENSITIES,
Abstract
An investigation of supersonic combustion as related to propulsive systems for high Mach number, high altitude flight is described. A method of laboratory simulation is employed which is considered to be suitable for fundamental studies of diffusional-controlled supersonic combustion under conditions approaching those of actual flight. A numerical analysis of the mixing and chemical reaction processes in a hydrogen-air ducted flow system was carried out, using a computer code based upon boundary layer concepts and including the effects of finite-rate chemistry. Results of the numerical calculations have indicated the inlet conditions at which auto-ignition is expected to occur within a reasonable combustor length. Based on the numerical data obtained, a constant area-divergent area combustion chamber was designed and fabricated for the performance of experimental tests under conditions closely matching those of the numerical study. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 29, 1968
- Accession Number
- AD0700759
Entities
People
- James E. Drewry
- Owen Fortune
- Raymond Edelman
- Robert G. Dunn
Organizations
- Air Force Research Laboratory