超音速/極超音速飛翔体周りの流れ場の新しい計算手法

概要

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A calculation method of flowfield around supersonic/hypersonic vehicles based on the finite element method (FEM) has been presented. In this study, the pressure term of Navier-Stokes equations was included in the flux vector. By performing this scheme, the pressure term could be expressed as a non-differential form in the weighted residual equations. This idea made it possible to calculate compressible flowfields including a shock wave with dramatic less error and better stability with a very small artificial viscosity, compared to conventional FEM calculations. The correctness of the present method was confirmed by comparing shock shapes obtained by the Schlieren system and by comparing streamlines obtained by the electric discharge method. The comparisons were carried out by investigating the flowfield around a Mach 10 MESUR capsule.
福山大学の論文