摘要
为了提高飞行器的隐身性能和降低其迎风阻力,采用具有平面腹部的低雷达截面外形机身与埋入式进气道的组合是一种良好的解决方案。但迄今尚未有成熟的平面埋入式进气道设计方法可供借鉴,为此对平面埋入式进气道口面参数进行了组合对比研究,旨在通过口面参数的选择来改善进气道的气动性能。在此基础上,选择一组口面参数设计了一梯形进口的平面埋入式进气道方案,并进行了高速风洞试验验证。研究结果表明:(1)进口侧棱决定了所产生的卷吸涡的强度,而前唇口导流角决定了进口段的横向压力梯度,两者均是驱动主流进入进气道内部的关键因素,为此对进气道总压恢复系数和周向畸变指数均有着重要影响;后唇口型线特征参数对进气道出口总压高低压区的分布起着调节作用,为此可以作为控制周向畸变指数的一种辅助措施。(2)合适的口面参数能明显改善平面埋入式进气道的性能。选取23°导流角、4°侧棱角以及30°后唇口型线特征参数组合进行了方案设计和风洞试验验证,在Ma0=0.7,α=-2°～8°,β=0°～2°的范围内,进气道的总压恢复系数在0.920～0.952之间,周向畸变指数在1.142%～2.237%之间,达到了实用水平。(3)研究范围内,攻角的增加有利于改善平面埋入式进气道的总压恢复系数和周向畸变指数。
In order to enhance the stealthy ability and reduce the drag of an aircraft, the combination of the stealthy fuselage of plane abdomen with a submerged inlet is a good approach. But the free stream is hard to enter the submerged inlet on the plane surface according to previous research. Therefore, for the improvement of the aerodynamic performance of this type inlet, effects of three important entrance parameters on the performance are investigated by wind-tunnel experiments and some useful conclusions are obtained. Then by selecting a group of suitable entrance parameters, a submerged inlet with the trapezoid entrance on the plane surface is designed and verified by wind tunnel tests. Results indicate：（1） The vortices generated by the two side edges and the transverse pressure gradient near the entrance caused by the ramp angle are two main forces which drive the free stream to enter the inlet and affect the inlet＇s performance apparently. Additionally, suitable aft lip can contribute to the reduction of the total pressure distortion by adjusting the distribution of the total pressure at the exit of the submerged inlet. （2） By selecting the ramp angle 23°, the side edge angle 4° and characteristic parameter of aft lip 30°, a submerged inlet on the plane surface is designed and validated. When Ma0 = 0.7,α=-2°-8°,β=0°-2°, the total pressure recovery coefficient ranges from 0. 920 to 0. 952 and the circumferential total pressure distortion index ranges from 1. 142% to 2. 237%, which shows clearly that the per- formance of the submerged inlet is acceptable. （3） The increase of attack angle is benefit to the total pressure recovery coefficient and the circumferential total pressure distortion, while small yaw does not bring obvious influence on the performance of the inlet.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2005年第3期268-275,共8页
Acta Aeronautica et Astronautica Sinica
基金
国防科技预研跨行业综合技术项目资助课题
关键词
进气道
平面埋入式进气道
口面参数
进口侧棱角
前唇口导流角
后唇口型线特征参数
总压恢复系数
周向畸变指数
inlet
submerged inlet on the plane surface
entrance parameter
side edge angle of the entrance
ramp angle
characteristic parameter of aft lip
total pressure recovery coefficient
circumferential total pres-sure recovery distortion index
