@inproceedings{oai:jaxa.repo.nii.ac.jp:00014324,
 author = {坪井, 伸幸 and 吹場, 活佳 and 嶋田, 徹 and Tsuboi, Nobuyuki and Fukiba, Katsuyoshi and Shimada, Toru},
 book = {宇宙航行の力学シンポジウム: 平成22年度, Symposium on Flight Mechanics and Astrodynamics: 2010},
 month = {Aug},
 note = {宇宙航行の力学シンポジウム 平成22年度 (2010年12月16-17日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, Symposium on Flight Mechanics and Astrodynamics,  2010 (December 16-17, 2010. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)), Sagamihara, Kanagawa Japan, Four preconditioned advective upwind splitting methods (AUSM) of low-diffusion flux-splitting schemes are applied to solve effectively at all speeds. The present inviscid fluxes use the preconditioned AUSMDV, AUSM(sup +)-up, SLAU, and SD-SLAU and the time integrations are the two stage Runge-Kutta and the LU-SGS method including preconditiiong method. The unsteady two-dimensional simulations around NACA0012 aerofoil show that the difference between these schemes is small and the calculated C(sub l) and C(sub d) do not agree with the expereimental data for alpha > 6 deg. The unsteady three-dimensional preconditioning simulations show that the present simulations predict the experimental data for higher angle of attack because the strong longitudinal vortices over the upper wing surface simulates in these unsteady three-dimensional simulations., 資料番号: AA0065106005},
 publisher = {宇宙航空研究開発機構宇宙科学研究所, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 title = {ハイブリッドロケット内部流れの解析に向けた前処理型非定常圧縮性低速流れ: 前処理型流束計算法と3次元流れの影響},
 year = {2011}
}