Nissan Motor Co. Ltd.
National Aerospace Laboratory
National Aerospace 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 SP-16
巻
16
ページ
27 - 32
発行年
1991-12
抄録（英）
Numerical solutions of the direct-simulation Monte Carlo (DSMC) method and the Navier-Stokes equation with a no-slip or a slip wall boundary condition are obtained for hypersonic rarefied monatomic gas flows in the transition regime (kn=0.1 - 0.001) around a finite-length parallel flat plate and a circular cylinder. A comparison among these numerical solutions indicates that the DSMC method is well applied to a fully continuum flow regime and the Navier-Stokes equation is applicable to the transition flow regime by the use of the slip wall boundary condition.
遷移領城流れのシミュレーション: DSMC法とNavier: Stokes数値解法
nalsp0016005.pdf
(1.34MB)
