Numerical Analysis of Scramjet Internal Flow by Hybrid Unstructured Grid Method

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概要

• 論文の詳細を見る

• Computations of internal viscous flowfields of scramjet models were conducted at inflow Mach numbers of 3.4 and 5.45. A hybrid unstructured grid method was used to compute the scramjet models with and without a short strut. The numerical method to solve the Navier-Stokes equations on the hybrid unstructured grid was developed using a finite volume cell vertex scheme and the lower-upper symmetric Gauss-Seidel (LU-SGS) implicit time integration algorithm. The computational results revealed that a thick subsonic region did not exist in the combustor near the top wall at Mach number 5.45. It was a desirable feature to avoid unstarting the engine. With the use of a strut, the relatively low velocity regions increased and the downward flow toward the cowl behind the step became strong. An overconcentration of fuel toward the top wall during weak combustion was observed in the experiment. The reason for this was that the airflow near the injector was turned to the top wall due to the small influence of combustion in the experiment.

• 一般社団法人日本機械学会の論文
• 2000-08-15

著者

• NAKAHASHI Kazuhiro

  Department of Aeronautics and Space Engineering, Tohoku University

• Hiraiwa Tetsuo

  Ramjet Propulsion Research Division National Aerospace Laboratory Kakuda Research Center

• Igarashi Yasutaka

  Kawasaki Heavy Industries Ltd.

• KODERA Masatoshi

  Ramjet Propulsion Research Division, National Aerospace Laboratory, Kakuda Research Center

• KANDA Takeshi

  Ramjet Propulsion Research Division, National Aerospace Laboratory, Kakuda Research Center

• MITANI Tohru

  Ramjet Propulsion Research Division, National Aerospace Laboratory, Kakuda Research Center

• Mitani Tohru

  Ramjet Propulsion Research Division National Aerospace Laboratory Kakuda Research Center

• Kodera Masatoshi

  Ramjet Propulsion Research Division National Aerospace Laboratory Kakuda Research Center

• Nakahashi Kazuhiro

  Department Of Aeronautics And Space Engineering Tohoku University

• Kanda Takeshi

  Ramjet Propulsion Research Division National Aerospace Laboratory Kakuda Research Center

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