V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL)
V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL)
V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL)
V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL)
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報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-669
巻
669
ページ
38
発行年
1981-05
抄録（英）
Wind tunnel tests were conducted of a rectangular wing of aspect ratio 6 with a NACA 0012 section to investigate side-force characteristics of a vertical rectangular winglet “A” or “B” mounted on the left wing tip. Winglet “A” has 1/10 the area of the wing. Winglet “B” has half the span of “A”. The installation angle of the winglets to the wing chord was variable up to ±20deg and the angle of the 1/3-chord flap up to ±30deg. Low speed (Reynold’s number 5×10(exp 5)) data were obtained over angles of attack of approximately ±15deg and at angles of sideslip of 0deg and ±10deg. The results indicate that winglets produce favourable side-force characteristics applicable to direct side-force control devices of aircraft in landing approaches particularly in cross-wind landings. In order to check the results, a simple formula has been proposed to calculate the induced side-force of a winglet by the lift of the main wing on the basis of the lifting line theory. It has been shown from the results that the differences of side-forces between upper left and lower right winglets or between normal and some variant winglets depend on the sign of pressure over the wing, the winglet and the plate on the top of the winglet.
Wind-tunnel Investigation of the Side-force of Rectangular Winglets on the Tip of a Rectangular Wing
naltr00669.pdf
(3.43MB)
