Two distinct but related basic research efforts are being investigated under the joint sponsorship of the U.S. Air Force Office of Scientific Research (AFOSR) and the U.S. Naval Sea Systems Command (NAVSEA). The first effort is to experimentally characterize the flowfields at the entrance of supersonic combustors in hypersonic dual-combustion ramjet engines and the second is to develop the component and engine cycle analysis required to predict the internal flowfields and performance of these engines. Both are basic to the successful development of advanced, hypersonic airbreathing engines. Progress to date includes the development of a simplified axisymmetric mixing and combustion analysis and a concomitant wall boundary layer analysis which describe the major flow phenomena within the main supersonic combustor of a dual combustion ramjet engine. The experimental hardware for the combustor/inlet interaction tests is also complete and initial testing has begun. Currently, refinements to the combustion and wall boundary layer analysis with particular emphasis on the base flow/mixing region, are being pursued and testing with the combustor/inlet interaction hardware continue. (kt)
Combustor/Inlet Interactions and Modeling of Hypersonic Dual Combustion Ramjet Engines
1983
22 pages
Report
No indication
English
Jet & Gas Turbine Engines , Combustion & Ignition , Ramjet engines , Supersonic characteristics , Supersonic combustion , Air breathing engines , Axisymmetric , Base flow , Boundary layer , Combustion , Combustors , Cycles , Flow fields , Hypersonic flight , Hypersonic vehicles , Inlets , Interactions , Internal , Mixing , Regions , Simplification , Test and evaluation , Walls
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