CONTROL OF ASYMMETRIC VORTICAL FLOWS OVER DELTA-WINGS AT HIGH ANGLES OF ATTACK

被引：12
作者：
WOOD, NJ
ROBERTS, L
CELIK, Z
机构：
[1] Stanford University, Stanford, CA
[2] Department of Aeronautics and Astronautics, University of Bath, Stanford, CA
[3] Department of Aeronautics and Astronautics, Stanford, CA
来源：
JOURNAL OF AIRCRAFT | 1990年 / 27卷 / 05期
关键词：
D O I：
10.2514/3.25294
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
Results from a wind tunnel experiment will be used to confirm that tangential leading-edge blowing is capable of controlling the vortical flow over a delta wing to very high angles of attack. The production of significant rolling moments and the ability to unburst a vortex has been demonstrated to 55-deg angle of attack. Strain gauge balance measurements and upper surface pressure distributions will be presented that illustrate the various modes of operation and that, in particular, identify the uncoupled/coupled nature of the vortex control at preand poststall angles of attack. At angles of attack beyond 40 deg, rolling moments are produced that exceed those produced by 20 deg of aileron deflection at 0-deg angle of attack. © 1990 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.
引用
收藏
页码：429 / 435
页数：7
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