Propulsion systems utilizing supersonic combustion have been recognized as having strong potential for vehicles operating in the hypersonic flight regime. Although ground facilities that would permit testing the complete engine rather than separate components are needed, it is not possible, within the present state-of-the-art, to ground test a complete engine under conditions duplicating all of the hypersonic flight parameters, particularly for a time duration sufficient to investigate the time-dependent facets of the combustion process. Thus, the use of some simulation technique is in order. It was felt that a requirement existed for a facility designed as well as possible to simulate the conditions in the combustor. An investigation of this simulation problem was undertaken in mid-1965. As a result of this investigation, a simulation technique and a facility to utilize this technique were developed. The facility described can simulate supersonic combustion conditions corresponding to flight at Mach numbers near 12. Only prolonged testing (up to 10 sec) is considered; gaseous hydrogen is the fuel. (Author)
Development of Facility for Supersonic Combustion Simulation
1967
7 pages
Report
Keine Angabe
Englisch
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