@inproceedings{oai:jaxa.repo.nii.ac.jp:00006641,
 author = {高野, 克倫 and 村山, 光宏 and 伊藤, 靖 and 中橋, 和博 and 松島, 紀佐 and Takano, Yoshimichi and Murayama, Mitsuhiro and Ito, Yasushi and Nakahashi, Kazuhiro and Matsushima, Kisa},
 book = {宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2003論文集, JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2003},
 month = {Mar},
 note = {The wing and flap have, generally, certain amounts of thickness at the trailing edge. It is known that the effect of the blunt trailing edge on the lift and drag coefficients of an airplane is not negligible. However, most of the flow computations of airplanes assume the sharp trailing edges because of the numerical cost in treating the blunt trailing edges. In this paper, the effect of trailing edge thickness of a 3D wing model is investigated. The DLR-F4 wing-body configuration that was used at the first AIAA CFD Drag Prediction Workshop is employed as a baseline model. In order to generate a high dense mesh around the wing especially at the trailing edge, the mesh refinement technique is effectively utilized. Computations of DLR-F4 with/without blunt trailing edge are performed at transonic cruising Mach number of M(sub infinity) = 0.75. In addition, chord extension models with sharp trailing edge are calculated. The computed results show that the flow structures near the trailing edge are significantly affected by the thickness of the trailing edge. This effect is larger in the wing tip region. The aerodynamic coefficients of the wing with blunt trailing edge are similar to that of the chord extension model with sharp trailing edge., 資料番号: AA0047427040, レポート番号: JAXA-SP-03-002},
 pages = {226--231},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {翼後縁厚みの全機空力係数への影響評価},
 volume = {JAXA-SP-03-002},
 year = {2004}
}