Computational Prediction of the Aerodynamic Characteristics of SSTO Vehicle Configurations

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概要

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• Flow-fields around basic SSTO-rocket configurations are numerically simulated by the Navier-Stokes computations. The study starts with the simulations of the Apollo-type configuration, in which the simulated results arecomparing with NASA's experiments and the capability of CFD approach is discussed.Computed aerodynamic coeffcients of Apollo configuration agree well with the experiments at subsonic, transonic and supersonic regime at all angles of attack and the present computational approach is validated.Effects of the configuration parameters on the aerodynamic characteristics are then numerically investigated and clarified in detail. It turns out that the aerodynamic characteristics of the body is mainly influenced by the location of the flow separation, the shock waves on the surface and the pressure level behind the body. Theshoulder radius of the body has strong influence to the Mach number dependency of the aerodynamic characteristics. The fineness ratio of the body mainly influences to the lift characteristics.

• 宇宙航空研究開発機構の論文

著者

• Kozo Fuji

  宇宙科学研究所 ]

• Keiichiro FUJIMOTO

  [ 東京大学大学院工学系研究科航空宇宙工学専攻

関連論文

• Computational Prediction of the Aerodynamic Characteristics of SSTO Vehicle Configurations

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