@article{oai:jaxa.repo.nii.ac.jp:00033240,
 author = {土井原, 良次 and 西田, 迪雄 and Doihara, Ryouji and Nishida, Michio},
 journal = {The Institute of Space and Astronautical Science report. S.P. : Aerodynamics, Thermophysics, Thermal Protection, Flight System Analysis and Design of Asteroid Sample Return Capsule},
 month = {Mar},
 note = {The 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., 資料番号: SA0200013000},
 pages = {43--52},
 title = {A Thermochemical Nonequilibrium Flow around a Super Orbital Reentry Capsule with Ablation},
 volume = {17},
 year = {2003}
}