Multiblock Navier-Stokes Solver for Wing/Fuselage Transport Aircraft
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概要
- 論文の詳細を見る
An implicit multiblock Navier-Stokes solver, which contains the LU-SGS subiteration method and the HLLEW scheme, has been developed for numerical simulations on complex and realistic aerodynamic configurations. Two-level halo cells are used to communicate data between abutting blocks. The transfinite interpolation (TFI) and the elliptic method with boundary control are employed to generate the initial multiblock grid and to smooth the grid distribution in each block. A comparison is first done for the AGARD supercritical LANN-wing with single- and multi-block grids. Then the present method is applied to a NASA transport wing/fuselage configuration and the NAL supersonic transport (SST) model. The choice of multiblock grid topology from the view of aeroelastic calculation and the comparison of Euler and Navier-Stokes solutions are investigated.
- 一般社団法人日本機械学会の論文
- 2002-02-15
著者
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Kondo Masahiro
Institute Of Fluid Science Tohoku University.
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Yang Guowei
Institute Of Fluid Science Tohoku University.
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Yang Guowei
Institute Of Fluid Science Tohoku University
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Obayashi Shigeru
Institute Of Fluid Science Tohoku University.
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Obayashi Shigeru
Institute Of Engineering Mechanics Tsukuba University
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- Preface
- Foreword(Advanced Fluid Information)
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