次世代超音速実験機設計におけるCFD-EFD相互検証(<小特集>数値計算と現実)

概要

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This paper presents a detailed comparison of CFD-EFD results for the supersonic flow around a next generation supersonic transport. The CFD results show fairly good agreement with each other as well as the experimental data except for following discrepancies : C_D, C_<Lα>, C_<Mα> and the pressure distributions at the leading edge on the upper surface as well as at the outer wing. Detailed studies on the above discrepancies were conducted as follows : sensitivity analysis for parameters of the experiments, repeatability check of the experimental data, geometry measurement of the wing tunnel model, aeroelasticity analysis of the wind tunnel model, and effects of transition. The results show that the discrepancies of C_<Lα> and C_<Mα> are caused by the aeroelastic deformation of the wind tunnel mode. Also the discrepancy of the pressure distributions are caused by the difference of the model geometry and the transition specification. The importance of mutual validation between CFD and EFD was shown through this study.
日本応用数理学会の論文
2004-12-22