2026-03-12T13:38:37Z https://jaxa.repo.nii.ac.jp/oai

oai:jaxa.repo.nii.ac.jp:00036650 2023-06-20T20:15:16Z 1887:1890 1896:1898:1899:1903

Computational Prediction of the Aerodynamic Characteristics of SSTO Vehicle Configurations FUJIMOTO, Keiichiro FUJIMOTO, Kozo 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. 資料番号: SA4585003000 宇宙科学研究所 Institute of Space and Astronautical Science 2003-09 eng departmental bulletin paper https://jaxa.repo.nii.ac.jp/records/36650 0285-6808 AA10632072 The Institute of Space and Astronautical Science report 682 1 31 https://jaxa.repo.nii.ac.jp/record/36650/files/SA4585003.pdf application/pdf 643.1 kB 2020-01-24