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HYPERSONIC PROPULSION INLETS FOR NASP APPLICATIONS
Title: INVESTIGATOR
Phone: () -
OVER THE PAST SEVERAL YEARS, IT HAS BEEN CLEARLY DEMONSTRATED THAT DEVELOPMENT OF TRANSATMOSPHERIC VEHICLES, SUCH AS THE NATIONAL AEROSPACE PLANE (NASP), WILL BE NECESSARY FOR A SUCCESSFUL SPACE-DEFENSE SYSTEM. IT IS ACCEPTED THAT THE DESIGN AND ANALYSIS OF SUCH VEHICLES WILL RELY HEAVILY UPON A DATA BASE GENERATED USING CFD TECHNIQUES. ACCURATE PREDICTIONS OF THE FLOWFIELD/CHEMISTRYLEADING UP TO AND THROUGH THE HYPERSONIC PROPULSION INLET WILL BE ESSENTIAL FOR RELIABLE PERFORMANCE/EFFICIENCY/TRADE ANALYSES OF THE PROPULSION CYCLE. IN PHASE I OF THIS EFFORT, WE WILL DEVELOP A THREE-DIMENSIONAL NON-EQUILIBRIUM PNS SCHEME FOR PREDICTING THE EXTERNAL FLOW OVER TYPICAL NASP-TYPE CONFIGURATIONS. THIS WILL PROVIDE A RELIABLE PREDICTION OF THE FLOWFIELD/CHEMISTRY ENTERING THE PROPULSION INLET. THE BASIC SOLUTION ALGORITHM IS INHERENTLY STABLE AND DOES NOT REQUIRE ANY SUB-LAYER APPROXIMATION. IN PHASE II OF THE EFFORT WE WILL EXTEND THIS PNS SCHEME TO PREDICT AXIALLY ATTACHED THREE-DIMENSIONAL NONEQUILIBRIUM INTERNAL INLET FLOWS.
* Information listed above is at the time of submission. *