OREX, orbital reentry experiment, base flow region, hypersonic flow, CFD, computational fluid dynamics, laminar nonequilibrium gas flow, MUSCL, monotonic upstream schemes for conservation laws, semi implicit method, TVD, total variation diminishing, source terms, species mass conservation equation, high enthalpy flow
Nagoya University Graduate School of Engineering
Nagoya University Graduate School of Engineering
Hitachi Ltd Mechanical Engineering Research Laboratory
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory (NAL)
雑誌名
航空宇宙技術研究所特別資料
雑誌名(英)
Special Publication of National Aerospace Laboratory
巻
29
ページ
128 - 133
発行年
1996-01
会議概要（会議名, 開催地, 会期, 主催者等）
航空宇宙技術研究所 8 Jun. 1995 東京 日本
会議概要（会議名, 開催地, 会期, 主催者等）（英）
National Aerospace Laboratory 8 Jun. 1995 Tokyo Japan
A CFD (Computational Fluid Dynamics) code has been developed to calculate a hypersonic flow around a reentry body including the base flow region. In order to inspect the CFD code, calculate problem 2 OREX (Orbital Reentry Experiment) 2-1, 2, 3 and 5 in this workshop. The problem 2-1, 2 and 3 are laminar non equilibrium gas flow. The result of problem 2-5 is used for the initial value of the reacting flow calculations of problem 2-2 and 3. For the thermally and chemically non equilibrium flow calculations, 11 species air is considered, along with the Park's two-temperature model. For the calculation of flowfield, the governing equations are full Navier-Stokes ones and are solved using a non MUSCL (Monotonic Upstream Schemes for Conservation Laws)-type second-order explicit upwind-TVD (Total Variation Diminishing) scheme by Harten-Yee. For the problem 2-1, 2 and 3, a semi-implicit method is applied to all species mass conservation equations because of stiff source terms.
High enthalpy workshop problem 2: OREX
nalsp0029011.pdf
(424.69KB)
