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SA0200013.pdf2.62 MB
titleA Thermochemical Nonequilibrium Flow around a Super Orbital Reentry Capsule with Ablation
Author(jpn)土井原, 良次; 西田, 迪雄
Author(eng)Doihara, Ryouji; Nishida, Michio
Author Affiliation(jpn)九州大学 工学部 航空工学科; 九州大学 工学部 航空工学科
Author Affiliation(eng)Department of Aeronautics and Astronautics, Kyushu University; Department of Aeronautics and Astronautics, Kyushu University
Issue Date2003-03
Institute of Space and Astronautical Science
Publication titleThe Institute of Space and Astronautical Science report. S.P.
Aerodynamics, Thermophysics, Thermal Protection, Flight System Analysis and Design of Asteroid Sample Return Capsule
Start page43
End page52
Publication date2003-03
AbstractThe aerodynamic heating to the super orbital reentry capsule of MUSES-C with ablation was numerically studied by using thermochemical nonequilibrium full viscous shock layer (VSL) equations. An 11 air-species model was used for non-ablating boundary conditions, and six carbonic species were added for ablating boundary conditions. With a three-temperature model, thermal nonequilibrium effect was taken into account. The convective and radiative heat fluxes to the wall were examined for both fully catalytic wall (FCW) condition and non-catalytic wall (NCW) condition at various altitudes for the capsule reentry trajectory path. The results of the ablation analysis at the altitude of 64 km showed that the stagnation heat fluxes with and without ablation are almost equal below the wall temperature of 3,000 K, whereas at the wall temperatures over 3,000 K, the stagnation heat flux is rapidly decreased with an increase in wall temperature due to significant sublimation.
Document TypeDepartmental Bulletin Paper
JAXA Category宇宙科学研究所

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