@inproceedings{oai:jaxa.repo.nii.ac.jp:00037856,
 author = {菊地, 勝浩 and 菊池, 秋広 and 柳澤, 三憲 and Kikuchi, Katsuhiro and Kikuchi, Akihiro and Yanagizawa, Mitsunori},
 book = {航空宇宙技術研究所特別資料, Special Publication of National Aerospace Laboratory},
 month = {Dec},
 note = {デルタ翼のまわりの流れの特性に関する計算方法を述べた。高後退角の翼がある程度以上の迎角を持つときは前縁から流れが剥離する。デルタ翼はスレンダーボディと考え得るのでスレンダーボディ理論を用いた。まず3次元翼形状から2次元断面形を切り出し、つぎに渦追跡法を用いて前縁剥離渦の位置と強さを求める。前縁剥離渦の効果を含めるためのモデルを提案した。本方法を用いてデルタ翼の空力特性を求め、実験結果と比較してよい一致をみた。, The method which allows the calculation of the characteristics for flow around a delta wing is described. Flow separations are certain to occur from the leading-edge on highly swept wings at moderate-to-high angles of attack. Since delta wing is considered as slender body, slender body theory is resorted. So first, two-dimensional cross sections are generated by slicing three-dimensional model and the position and strength of leading-edge separation vortices is determined using vortex tracking method. In order to include the effect of leading-edge separation vortex a model is proposed. Some aerodynamic coefficients of delta wing are obtained from the present method and comparisons between numerical and experimental results show good agreement., 資料番号: AA0004174019, レポート番号: NAL SP-27},
 pages = {153--158},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {境界要素法による前縁はく離渦の効果を入れたデルタ翼の空力計算},
 volume = {27},
 year = {1994}
}