超音速/極超音速飛翔体周りの流れ場の新しい計算手法(流体工学,流体機械)

概要

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A new calculation method of flow field around supersonic/hypersonic vehicles is developed based on the finite element method (FEM) scheme. In the case of general simulations by the FEM, the pressure P is expressed by a differential form, and therefore, there occurs a considerable discrepancy. Moreover, it is generally said that the memories and the speed of the calculations are worse than the finite differential method (FDM). However, in this study, the pressure term is included in the flux vector expressing by the stress tensor. By this treatment, the pressure term can be expressed as a non-differential form by applying the weighted residual method. From this method, the flowfield around a supersonic/hypersonic vehicles can be successfully calculated with high speed, little discrepancies, and stability. The propriety of our method was examined by comparing the numerical results with the one of experiments obtained by the schlieren method and the electric discharge method. The comparisons were carried out under the conditions that the Mach number was 10, and a wedge model and a re-entry capsule were used to compare. From these comparisons, it was found that the calculated shock shapes and streamlines were in good agreement with the experimental results.
一般社団法人日本機械学会の論文
2004-04-25