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Optimal Supersonic Diffuser Design of Integrated Rocket Ramjet Engine  

민병영 (건국대학교 항공우주공학과 대학원)
이재우 (건국대학교 항공우주공학과)
변영환 (건국대학교 항공우주공학과)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.6, no.2, 2002 , pp. 65-74 More about this Journal
Abstract
Optimal supersonic diffuser shape of integrated rocket ramjet engine was derived which maximizes the total pressure recovery. Mass flux is considered as a design constraint and the second oblique shock angle of the external ramp, the cowl-lip angle and the throat area are selected as design variables. Refined response surface method through design space transformation technique was developed and employed, and high confidence level of the regression model could be obtained. Genetic algorithm was implemented for both system optimizer and subspace regression model optimization. Virtual nozzle was located at the end of throat to adjust the back pressure. With only 20 aerodynamic analyses, optimal supersonic diffuser shape which has 14% improved total pressure recovery characteristics was successfully designed.
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