@inproceedings{oai:jaxa.repo.nii.ac.jp:00006450,
 author = {松山, 新吾 and 澤田, 恵介 and Matsuyama, Shingo and Sawada, Keisuke},
 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2004論文集, JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2004},
 month = {Mar},
 note = {A trajectory-based heating analysis of the Galileo probe entry flowfield is attempted to reproduce the heatshield recession data obtained during the entry flight. In the present calculation, the mass conservation equations for the freestream gas (hydrogen-helium gas mixture) and the ablation product gas are solved with an assumption of thermochemical equilibrium. The ablation process is assumed to be quasi-steady and is coupled with the flowfield calculation. The radiative energy transfer calculation is tightly coupled with the flowfield calculation, where the absorption coefficients of the gas mixture are given by the multiband radiation model having 4,781 wavelength points for wavelength range from 750 to 15,000 A. The injection-induced turbulence model proposed by Park is employed to account for the enhanced turbulence effect due to the ablation product gas. It is shown that the final recession profile of the flight data at the frustum region can be closely reproduced if the injection-induced turbulence model is employed, although that at the stagnation region is overestimated. The cause of the enhanced radiative heating that occurs at the frustum region is given in connection with the enhanced turbulence effect in the shock layer., 資料番号: AA0048469010, レポート番号: JAXA-SP-04-012},
 pages = {63--68},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {ガリレオ探査衛星突入飛行時のアブレータ損耗量再現の試み},
 volume = {JAXA-SP-04-012},
 year = {2005}
}