@inproceedings{oai:jaxa.repo.nii.ac.jp:00004737,
 author = {牧野, 好和 and 大平, 啓介 and 牧本, 卓也 and 三友, 俊輝 and Makino, Yoshikazu and Ohira, Keisuke and Makimoto, Takuya and Mitomo, Toshiteru},
 book = {宇宙航空研究開発機構特別資料: 第42回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2010 論文集, JAXA Special Publication: Proceedings of 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010},
 month = {Feb},
 note = {第42回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2010 (2010年6月24日-25日. 米子コンベンションセンター BiG SHiP), 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010 (June 24-25,  2010. Yonago Convention Center BiG SHiP), Yonago, Tottori Japan, Effects of static aeroelastic deformation of a wind-tunnel test model on the aerodynamic characteristics are discussed in wind-tunnel tests in the preliminary design phase of the silent supersonic technology demonstrator (S3TD). The static aeroelastic deformation of the main wing is estimated for JAXA 2m x 2m transonic wind-tunnel and 1m x 1m supersonic wind-tunnel by a finite element method (FEM) structural analysis in which its structural model is tuned with the model deformation calibration. Aerodynamic load of the wing and the deformation effects on the aerodynamic forces are estimated by a simple aerodynamic model in which the surface pressures of the wing are interpolated from some Euler CFD calculation results of different angle of attacks. The estimated deformation effects improve the agreement of the measured and predicted aerodynamic performance. Further development of the aerodynamic/structural estimation tool for wind-tunnel testing is advanced by the full potential aerodynamic analysis tool and FEM structural analysis tool in order to improve the accuracy of the deformation effects evaluation in view of the efficiency for the practical application. The results of the wing deformation estimated by the normal iteration of the aerodynamic and structural analysis agree well with those estimated by the simple aerodynamic model., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064967030, レポート番号: JAXA-SP-10-012},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {静粛超音速研究機基本全機風試における模型静的空力弾性変形効果について},
 volume = {JAXA-SP-10-012},
 year = {2011}
}