EXPERIMENTAL-STUDY OF EFFECTS OF FOREBODY GEOMETRY ON HIGH ANGLE-OF-ATTACK STABILITY

被引：31
|
作者：
BRANDON, JM
NGUYEN, LT
机构：
[1] NASA Langley Research Cent, United States
来源：
JOURNAL OF AIRCRAFT | 1988年 / 25卷 / 07期
关键词：
Aerodynamics--Stability - Aircraft Models - Flow of Fluids--Vortex Flow - Wind Tunnels;
D O I：
10.2514/3.45628
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
A series of low-speed wind-tunnel tests on a generic airplane model with a cylindrical fuselage are made to investigate the effects of forebody shape and fineness ratio, and fuselage/wing proximity on static and dynamic lateral/directional stability. During the stability investigation ten forebodies were tested including three different cross-sectional shapes with fineness ratios of 2, 3, and 4. The results show that the forebody cross-sectional shape and fineness ratio and forebody/wing proximity can strongly affect both static and dynamic (roll) stability at high angles of attack. These characteristics result from the impact of these factors on forebody vortex development, the behavior of the vortices in sideslip, and their interaction with the wing flowfield.
引用
收藏
页码：591 / 597
页数：7
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