National Aerospace Laboratory
National Aerospace Laboratory
Mitsubishi Heavy Industries Ltd.
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所特別資料
雑誌名(英)
Special Publication of National Aerospace Laboratory SP-8
巻
8
ページ
91 - 102
発行年
1987-11
抄録（英）
A boundary element method is presented for determining aerodynamic loadings on arbitrary configurations in oscillatory subsonic flow. Formulas (modified Morino's method) are given for the unsteady pressure distributions or unsteady force experienced in subsonic flow by the wing-store combination, oscillating in the torsional oscillations about a fixed axis parallel to the span and other oscillating modes (flapping, plunging). Interference effects from an underwing pylon store were analyzed. The method is finally verified through comparison with experiment for the model at angles of attack from -5 degree to +5 degree, and reduced frequencies from 0.65 to l.3 at low subsonic flow.
境界要素法による全機形態の非定常空力計算
nalsp0008013.pdf
(702.25KB)
