Studies Leading to the Realization of Supersonic Combustion in Propulsion Applications.
Abstract
The report discusses theoretical and experimental studies of hydrogen mixing and combustion in a high enthalpy (6000K) Mach 3.5 airstream carried out in a combustion driven hypersonic shock tunnel operating with a tailored primary shock Mach number of 10.2 - 10.6. Results obtained using wall static pressure measurements indicated that following injection there was a steep compression zone, followed by a re-expansion zone after which the static pressure gradually increased to approach that predicted by complete combustion at test conditions. Direct glow photographs showed clearly positions of heat release zones for the two separate injector configuration. Results obtained from a high response gas composition probe placed in the injector wakes, showed that the hydrogen concentration was smallest in the vortex generator wake at a given axial distance downstream of injection. These results showed that for given fuel throughout the vortex generating injector produced the most efficient mixing.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1972
- Accession Number
- AD0746341
Entities
People
- J. Swithenbank
- M. T. Jacques
- R. Payne
Organizations
- University of Sheffield