@inproceedings{oai:jaxa.repo.nii.ac.jp:00014454,
 author = {坪井, 伸幸 and 吹場, 活佳 and Tsuboi, Nobuyuki and Fukiba, Katsuyoshi},
 book = {宇宙航行の力学シンポジウム, Symposium on Flight Mechanics and Astrodynamics},
 month = {Dec},
 note = {宇宙航行の力学シンポジウム(平成20年度)(2008年12月4～5日、宇宙航空研究開発機構宇宙科学研究本部), Symposium on Flight Mechanics and Astrodynamics 2008 (December 4-5, 2008. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)), Sagamihara, Kanagawa Japan, A preconditioned advective upwind splitting method (AUSM) of low-diffusion flux-splitting schemes is applied to solve effectively at all speeds in liquid rocket chambers. The present flux uses the preconditioned AUSM-DV and the time integrations are the two-Stage Runge-Kutta and the LU-SGS method including preconditioning method. The present steady-state simulations can solve the low speed flows around the NACAOO12 aerofoil effectively. The unsteady low speed flow around a cylinder can be simulated and the calculated C(sub l),C(sub d) and S(sub t) agree well with the other researchers' results., 資料番号: AA0064729031},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 title = {前処理法による非定常圧縮性低速流れの数値解析},
 volume = {平成20年度},
 year = {2009}
}