@inproceedings{oai:jaxa.repo.nii.ac.jp:00006147,
 author = {鈴木, 俊之 and 山田, 哲哉 and 酒井, 武治 and 山本, 行光 and Suzuki, Toshiyuki and Yamada, Tetsuya and Sakai, Takeharu and Yamamoto, Yukimitsu},
 book = {宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2005論文集, JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2005},
 month = {Feb},
 note = {An integrated numerical method to obtain thermal response of ablator under aerodynamic heating environment is briefly described. In this method, a two-dimensional thermal response analysis code, namely SCMA2, is loosely coupled with a thermochemical nonequilibrium CFD code. The method is applied to reproduce the thermal response of ablator obtained by the heating tests conducted in the 1 MW arc-jet wind tunnel facility at ISAS/JAXA. Surface temperature, heat flux variation and surface shape change of the ablative test piece under arc-jet flow condition are calculated by the integrated code. These obtained results are compared with those given by one-dimensional SCMA code, and also with the experimental data for the purpose of validation. As to the comparison of calculated surface temperature with experimental data, quantitative agreement is yet to be accomplished because of the uncertainties in freestream conditions and material surface conditions. However, obtained results show that the present coupled approach is still available to predict the thickness of ablator required for space vehicles in future missions., 資料番号: AA0049212014, レポート番号: JAXA-SP-05-017},
 pages = {88--93},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {アブレータ供試体周りの流れ場とアブレータ熱応答との連成解析},
 volume = {JAXA-SP-05-017},
 year = {2006}
}