@inproceedings{oai:jaxa.repo.nii.ac.jp:00037244,
 author = {望月, 修 and Mochizuki, Osamu},
 book = {航空宇宙技術研究所特別資料, Special Publication of National Aerospace Laboratory},
 month = {Jan},
 note = {30 Sep.-1 Oct. 1997 (21st). 26-27 Mar. 1998 (22nd), 30 Sep.-1 Oct. 1997 (21st). 26-27 Mar. 1998 (22nd), ピッチングアップおよびピッチングダウン運動中のNACA0020翼の動的失速を翼前縁近傍の薄スリットから上面に沿った壁面噴流によって制御した。レイノルズ数は翼弦cと主流速度Uに基づき、8.6×10(exp 4)である。この翼は、低減ピッチ速度Ω=ωc/(2U)(ωはピッチ速度(rad/s))が0.012で、迎角が0から30度の間のピッチングアップおよびピッチングダウン運動に耐えた。1周期中の吹出し量は一定吹出しの場合の47%で、比例吹出しの場合の78%である。, Dynamic stall of a NACA0020 airfoil in pitching up and pitching down motion is controlled by a wall jet along the upper surface from a thin slit near the leading edge. The Reynolds number, based on the airfoil chord, c, and the free stream velocity, U, is 8.6 x 10(exp 4). The airfoil underwent pitching up and pitching down motion between angle of attack of 0 to 30 degrees at a reduced pitch rate, Omega (equals to omega x c/(2U), where omega is pitch rate (rad/s)) of 0.012. The amount of the injection during one period is 47 percent of that of the constant injection and 78 percent of that of the proportional injection., 資料番号: AA0001655021, レポート番号: NAL SP-40},
 pages = {81--82},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {動的失速の最適制御},
 volume = {40},
 year = {1999}
}