Computation of Three-Dimensional Chemically Reacting Viscous Flow around Rocket Body

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概要

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• A hybrid scheme that treats the strong peripheral shock as sharp shock is developed to compute the hypersonic, viscous and chemically reacting three-dimensional flow around a rocket body. A multi-component mixture of thermally perfect but calorically imperfect gas is used. Diffusion velocities at all grid points are computed by solving multi-component diffusion equations. All the molecular diffusion transport terms are retained. The governing equations in conservation-law form are solved using a non-iterative, approximately-factored implicit finite-difference scheme. Both fully-catalytic and non-catalytic walls are treated. Laminar flowfields over a rocket nose configuration are generated for different gas models and boundary conditions.

• 宇宙航空研究開発機構の論文

著者

• Fujiwara T.

  Nagoya University.

• REDDY K.

  Nagoya University.

• OGAWA T.

  National Aerospace Laboratory.

• ARASHI K.

  Mitsubishi Heavy Industries.

関連論文

• Computation of Three-Dimensional Chemically Reacting Viscous Flow around Rocket Body

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