Numerical Simulation on Unsteady Compressible Low-Speed Flow Using Preconditioning Method for Hybrid Rocket: Efects of Preconditioning Fluxes and Three-dimensional Flow
Kyushu Institute of Technology
Muroran Institute of Technology
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
出版者
宇宙航空研究開発機構宇宙科学研究所
出版者（英）
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)
雑誌名
宇宙航行の力学シンポジウム: 平成22年度
雑誌名(英)
Symposium on Flight Mechanics and Astrodynamics: 2010
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
抄録（英）
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.
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
