摘要
在双三角翼、椭圆机身的冀身融合体气动布局中配置二元矢量喷管,本文对该布局形式的矢量喷流和主流绕流之间的干扰流场及其对机翼气动特性的影响进行了系统的实验研究。结果表明,矢量喷流对主流及其气动特性的干扰效应可以分为三类:矢量喷流对附流的干扰效应仅限于喷口附近,主要表现为引射或阻塞作用;矢量喷流对前缘涡的干扰效应起稳定旋涡的作用,这样对稳定涡系的干扰影响很弱,但对破裂涡绕流的干扰效应较强,且随喷流矢量角的增大而增强。
Thrust vectoring/reversing technique is one of important technologies to develop next generation of fighter. Present experimental study is to investigate the interaction between vectoring jet flow and main flow around aircraft model. This interaction strongly depends on nozzle/airframe configuration geometry. In the present configuration vectoring jet effects on the aerodynamic behavior of the wing can be divided into three types;jet effects in the attached main flows of the wing are limited in the area near the nozzle exit; jet effects in the stable leading edge vortics flows are weak on the vortics and vectoring jet effects can not increase the strength of the stable vortices; jet effects in the bursted vortices flows can recover to the stable vortices due to reducing the adverse pressure gradient along the vortex axis and the pressure distribution on the wing can be improved.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
1993年第1期63-72,共10页
Journal of Beijing University of Aeronautics and Astronautics
关键词
二元喷管
矢量喷流
涡流干扰
机翼
two dimensional nozzle, vectoring jet, vectoring jet/vortex flow intercation.
