This report describes the experimental data and the procedures used in acquiring and reducing the thermal loads data during tests of a hydrocarbon- fueled scramjet combustor at United Technologies Research Center (UTRC). This research effort is part of the UTRC effort to develop dual-mode scramjet combustor technology to support the development of Mach S missile technology. The objective of the thermal loads testing was to map the thermal and mechanical loads, including heat transfer, dynamic and static pressures, and skin friction in a scramjet combustor during direct-connect scramjet tests. The tests were conducted at the UTRC Ramject/Scramjet direct-connect combustor test facility in East Hartford, CT.
Thermal Performance of a Scramjet Combustor Operating at Mach 5.6 Flight Conditions
1997
145 pages
Report
Keine Angabe
Englisch
Physics , Jet & Gas Turbine Engines , Aircraft , Aerodynamics , Thermal properties , Heat transfer , Supersonic combustion ramjet engines , Thermal stresses , Test and evaluation , Experimental data , Performance(Engineering) , Loads(Forces) , Research facilities , Combustors , Fuels , Ramjet engines , Hydrocarbons , Mach number , Dual mode , Static pressure , Dynamic pressure , Skin friction , Scramjet combustor
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