An Aerodynamic Redesign of the SR-71 Inlet with Applications to Turbine Based Combined Cycle EnginesAn Aerodynamic Redesign of the SR-71 Inlet with Applications to Turbine Based Combined Cycle Engines
【title】：An Aerodynamic Redesign of the SR-71 Inlet with Applications to Turbine Based Combined Cycle EnginesAn Aerodynamic Redesign of the SR-71 Inlet with Applications to Turbine Based Combined Cycle Engines 【作者】：Colville, Jesse; Lewis, Mark; Maryland, Univ., College Park 【Corportate Author】：【Catalog】：20 Spacecraft Propulsion and Power (AH)【Keywords】：COMBINED CYCLE ENGINES; Turbine engines; Engine design; Aerodynamic characteristics; Engine inlets; TWO STAGE TO ORBIT VEHICLES; Reusable launch vehicles; Supersonic inlets; Hypersonic inlets; Engine parts【Publish Year】： 【Language】：English【Record id】：2004_3481; A04-34899【File Size】：617K 【Come From】：40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit; Fort Lauderdale, FL; July 11-14, 2004.【AAIA ID】：2004_3481 【Abstract】：Performance considerations for a turbine-based combined-cycle engine inlet are presented using the inlet of the Lockheed Martins SR-71 as a baseline. External flow analysis and self-starting characteristics of the inlet have been quantified for the original intended flight regime with a maximum shock-on-lip at Mach 3.2. A series of modifications are considered for their ability to extend the range of the inlet into the hypersonic flight regime. Self-starting characteristics of these new designs are characterized, including two that would be able to remain self-started into the Mach 6-7 range. The use of external isentropic compression was also considered as a means to improve the performance of the original inlet; this technique has the ability to deliver the freestream supersonic flow to the turbine compressor and/or ram burner more efficiently than traditional inlet designs.
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