Numerical Study on Aerodynamic Heating Reduction by Opposing Jet
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概要
- 論文の詳細を見る
A numerical study on a reduction of aerodynamic heating by opposing jet insupersonic and hypersonic flow has been conducted. Flow field around ahemisphere model is calculated in the free stream of Mach number of 4 ands 8.The coolant gas is injected through the nozzle at the nose of the model. Innumerical analysis, axisymmetric Navier-Stokes equations are solved with k-ωturbulence model. Flow structures at various conditions are investigated andflow mechanisms of reduction of aerodynamic heating are revealed. Alsooptimal jet conditions for the reduction of aerodynamic heating are obtained.According to the investigation of various conditions of opposing jet, importantphenomena of flow field and some effective jet conditions are found. It becomesclear that a performance of the thermal protection system by opposing jet isgreatly affected by jet conditions.
- 九州大学の論文
- 2006-03-23
著者
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Hayashi Kentaro
Department Of Neurosurgery Nagasaki University School Of Medicine
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ASO Shigeru
Department of Aeronautics and Astronautics
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Tani Yasuhiro
Department Of Aeronautics And Astronautics Faculty Of Engineering Kyushu University
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Hayashi Kentaro
Department Of Aeronautics And Astronautics Graduate School Of Engineering Kyushu University
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Hayashi Kentaro
Department Mechanical Engineering For Computer-controlled Machinery Osaka University
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ASO Shigeru
Department of Aeronautics and Astronautics, Faculty of Engineering, Kyushu University
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