@inproceedings{oai:jaxa.repo.nii.ac.jp:00005634,
 author = {横川, 譲 and 村山, 光宏 and 伊藤, 健 and 山本, 一臣 and Yokokawa, Yuzuru and Murayama, Mitsuhiro and Ito, Takeshi and Yamamoto, Kazuomi},
 book = {宇宙航空研究開発機構特別資料: 第39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2007論文集, JAXA Special Publication: Proceedings of 39th Fluid Dynamics Conference/Aerospace Numerical Simulation Symposium 2007},
 month = {Feb},
 note = {This report presents experimental data obtained in lowspeed wind tunnel testing for high-lift configuration aircraft model JSM (JAXA Standard Model). Two time of the testing were conducted at 6.5 m by 5.5 m Low-speed Wind Tunnel in JAXA (JAXA-LWT1) aiming to store validation data for CFD (Computational Fluid Dynamics) analysis and to observe flow physics on high-lift system. JSM is a half type model which assumes 17 percent similarity of a modern 100-passenger class regional jet airliner. The model is equipped with leading edge slat, double-slotted flap at the inboard and single-slotted flap at the outboard, flow-through nacelle, in addition, a circular fuselage and Flap Track Fairings (FTF) so that the detailed flow fields occurring in actual aircraft can be provided. At first, repeatability and sensitivity of the force and the moment data in the case the detail of the model was slightly changed were assessed as well as the accuracy was confirmed from large amount of data in the first and the second testing. Variation in lift performances between long-cowling nacelle and short-cowling nacelle was observed with couple of the measurements and visualizations. The results showed much better stall performances of the short-cowling configuration than the long-cowling one that was due to less interference between the nacelle pylon and the wing. Boundary layer tripping on flap could clarify the loss in aerodynamic performances. Finally, improvement of stall characteristics by a vortex generator and an efficient way to decide its installation location by the application of Kriging based Genetic Algorithm (GA) on nacelle was discussed., 資料番号: AA0063742028, レポート番号: JAXA-SP-07-016},
 pages = {172--177},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {JAXA高揚力装置半裁模型の風洞試験と空力特性},
 volume = {JAXA-SP-07-016},
 year = {2008}
}