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Span Load Distributions Resulting From Angle of Attack, Rolling, and Pitching for Tapered Sweptback Wings With Streamwise Tips. Supersonic Leading and Trailing Edges.

机译：使用streamwise提示的锥形后掠翼的攻击角度，滚动角度和俯仰角度导致的跨度载荷分布。超音速前缘和后缘。

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作者
Martin, J. C.; Jeffreys, I.;
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年度 1952
页码 1-146
总页数 146
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
Load distribution; Angle of attack; Leading edges; Taper; Supersonic characteristics; Sweptback wings; Trailing edges; Aq m00-10-3287;

机译：载荷分布;迎角;前缘;锥度;超音速特征;后掠翼;后缘; aq m00-10-3287;
入库时间 2022-08-29 11:44:13

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3. Numerical simulation of flow over delta wing with trailing-edge jet at high angle of attack [J] . Z. K. Zhang, H. S. Tang International Journal for Numerical Methods in Engineering . 2004,第15期

机译：高攻角后缘射流在三角翼上流动的数值模拟
4. Streamwise Momentum Analysis of Subsonic Wall Interference on Flat- Plate Wings at High Angles of Attack [C] . M. Mokry AIAA Aerospace Sciences Meeting and Exhibit . 2004

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5. Modeling the rolling moment on the 65-degree delta wing for rolling motions at high angle of attack. [D] . Myatt, James Harold. 1997

机译：对65度三角翼上的侧倾力矩进行建模，以实现高攻角下的侧倾运动。
6. Some Effects of Taper Ratio on the Transonic Flutter Characteristics of a Series of Thin Cantilever Wings Having a Sweptback Angle of 45° and an Aspect Ratio 4.0 [O] . Eiichi NAKAI, Toshiro TAKAGI, Yasukatsu ANDO 1966

机译：锥形比对一系列薄悬臂机翼的横向振荡特性的一些效果，其具有45°的扫频角和纵横比4.0

Span Load Distributions Resulting From Angle of Attack, Rolling, and Pitching for Tapered Sweptback Wings With Streamwise Tips. Supersonic Leading and Trailing Edges.

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