@inproceedings{oai:jaxa.repo.nii.ac.jp:00005405,
 author = {横川, 譲 and 村山, 光宏 and 内田, 洋 and 伊藤, 健 and 山本, 一臣 and Yokokawa, Yuzuru and Murayama, Mitsuhiro and Uchida, Hiroshi and Ito, Takeshi and Yamamoto, Kazuomi},
 book = {宇宙航空研究開発機構特別資料: 第40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2008論文集, JAXA Special Publication: Proceedings fo 40th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2008},
 month = {Feb},
 note = {第40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2008. 会期: 2008年6月12日-6月13日. 会場: 東北大学片平キャンパス, This report summarizes experimental results obtained in lowspeed wind tunnel testing for high-lift configuration aircraft model JSM (JAXA highlift configuration Standard Model). Following two time of the testing, third testing was implemented at 6.5 m by 5.5 m lowspeed wind tunnel in JAXA (JAXA-LWT1) in order to acquire validation data for CFD and to observe flow physics on high-lift system. JSM is a half type model which assumes 17 % 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 of the force and the moment data throughout two times of the testing where the short-cowling nacelle was used was checked. Variation in aerodynamic performances between two kinds of flap deflection angle was tested. The results showed reduction of separation on the flap in the case of 30 degree, which is expected to be useful for CFD validation. Following that, effects of the nacelle installation and configuration of the slat root were observed. When the nacelle was installed, lift performance was not largely changed whether slat root was connected to the fuselage or not. On the contrary to that, maximum lift coefficient and stall angle of attack were increased by slat root connection. In that case, separation pattern at the stall was also affected., 形態: カラー図版あり, 資料番号: AA0064303003, レポート番号: JAXA-SP-08-009},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {JAXA高揚力装置標準模型空力解析のための検証風洞試験},
 volume = {JAXA-SP-08-009},
 year = {2009}
}