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A CFD (Computational Fluid Dynamics) workshop was held in the 44th Aircraft Symposium, October 2006, in order to evaluate domestic CFD technology for civil transport aircrafts in high-lift configurations. JAXA provided an experimental data for comparison obtained in the JAXA large low-speed wind tunnel using a half model equipped with high-lift devices, fuselage, nacelle-pylon, slat tracks and Flap Track Fairings (FTF). This paper briefly presents the experimental model, objectives and test cases of the CFD workshop, summary of comparison, and obtained knowledge and issues on CFD and wind tunnel testing for high-lift configuration., 資料番号: AA0063742027, レポート番号: JAXA-SP-07-016

航空宇宙技術研究所 10-11 Jun. 1993 東京 日本, National Aerospace Laboratory 10-11 Jun. 1993 Tokyo Japan, 「3次元課題:ONERA(フランス国立航空宇宙研究所)M-5翼まわりの流れの解析」の結果報告を与えた。提出された計算結果の全ては、相互および実験データとの差をみるためそれぞれの図により示された。「課題A:一様流マッハ数0.84、迎角α=-1度、レイノルズ数1×10｛6｝で自由遷移の場合」および「課題B:一様流マッハ数0.84、迎角α=-1度、レイノルズ数6×10｛7｝で全面乱流の場合」において、圧力分布および揚力面と胴体上の等圧線とを比較した。レイノルズ数1×10｛6｝における実験データも示した。課題Aにおいて主翼上における境界層遷移線を比較した。「課題C:模型機体空力特性の計算」では、CL〜α、CL〜CD、CL〜CM曲線を実験データと比較して示した。これらの結果に導く要因および今後に必要な改良について論じた。, Compendium of results of three dimensional problem; flow analysis around ONERA M5 (Office National d'Etudes et d'Recherches Aerospatiales) configuration is given. All of the submitted computation results were shown on the respective figures to see the differences between the computed results and experimental data. In Problem A; flow analysis with freestream condition of Mach number, 0.84. alpha = minus one deg, Reynolds number. 1 X 10(exp 6) with free transition condition and Problem B; flow analysis with freestream condition of Mach number, 0.84, alpha = minus one deg, Reynolds number. 6 X 10(exp 6) with fully turbulent conditions. the pressure distributions and Cp contours on the lifting surface and the fuselage were compared. Experimental data with Reynolds number 1 X 10(exp 6) were also shown. In Problem A. the computed transition lines of the main wing surface were compared. In Problem C: computation of aerodynamic characteristics of the Model aircraft, the C(sub L) - alpha, C(sub L) - C(sub D) and C(sub L) - C(sub M), curves were shown in comparison with experimental data. The factors leading to the present results were discussed and necessary future improvement were also discussed., 資料番号: AA0004171010, レポート番号: NAL SP-22

航空宇宙技術研究所 10-11 Jun. 1993 東京 日本, National Aerospace Laboratory 10-11 Jun. 1993 Tokyo Japan, 航技研(NAL)特別資料SP-20に述べられた「2次元部門課題:Garabedian-Korn翼型」に対する結果報告の要約を与えた。SP-20では、提出された全ての計算結果を相互の差が分るように図にプロットした。「課題A:設計点での計算」について特に論じた。圧力分布はかなりよく一致するものの、翼弦方向の乱流境界層の特性、速度プロフィール、境界層および伴流における渦粘性係数はかなりばらつくことが判明した。そのような結果になる要因および今後に改良すべき点を論じた。本報告では結論のみを示した。, A summary of the Compendium of results of two dimensional problem: Garabedian-Korn Airfoil reported in NAL SP-20 is given. In NAL SP-20 all of the submitted computation results were plotted on the respective figures to see the differences. Problem A: Design point computation was discussed significantly. Although pressure distribution gives fairly good agreement, turbulent boundary layer characteristics along chord, velocity profiles and eddy viscosity coefficient distributions in the boundary layer and wake disclosed scattered variation. The factors leading to the present results were discussed and required future improvement is discussed. In this paper only the conclusion is shown., 資料番号: AA0004171009, レポート番号: NAL SP-22