タイトル（掲載誌）航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-1072
一般注記出版タイプ： NA
A wind tunnel test of a three-dimensional swept-back wing with suction laminar-flow-control was executed to investigate the drag reduction effect of the LFC under various test conditions. The wing model has a hybrid suction surface which consists of a porous surface with very fine holes from near the leading edge to 25％ chord and a slotted surface with a large number of fine slots from 25％ chord to 80％ chord. Total drag CDT, which is defined as the sum of the wake drag and the equivalent drag, was measured for various suction quantities. Application of the optimum suction quantities, which were determined so as to delay the natural transition points to 90％ chord with the minimum total suction quantity for each test conditon, gives a fairly large drag reduction(about 40％) compared with the no suction case for Reynolds numbers up to 3.6×10(exp 6). A suction applied only in the leading edge region also gives not a little drag reduction, but a suction in the rear part of the wing where the boundary layer flow is already turbulent has no effect on the drag reduction. It has been observed that when there is no suction the porous suction surface generates much earlier transitions than does the solid surface. As transition is a very important problem for practical application of LFC, further investigation will be required.
資料番号: NALTR1072000
レポート番号: NAL TR-1072
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ