摘要
S弯进气道由于其良好的隐身性能为现代作战飞机所青睐,但是由于进气道是弯曲的,较大的表面曲率容易导致边界层分离,降低了进气道的总压恢复,增加了气流的湍流脉动,导致旋流畸变的发生。对边界层流动实施控制可以推迟、扼制流动分离,改变进气道的气动性能。本研究在某机型进气道的CAD模型的基础上,利用FLUENT软件对采用不同类型的边界层扰流片(涡流发生器)进行数值模拟,控制边界层分离,使大S弯进气道出口的总压恢复和旋流畸变指标得以改善。
S-inlet has good performance of stealth which is favoured by modern battleplan, at the same time the bend inlet and big exterior curvature wil lead to boundary layer separation, lower total pressure, increase the grade of pulsantt urbulence, ifnal y cause the swirl distortion. Boundary layer control wil put off lfow separation and give a good performance of inlet. Based on the CAD model of a battleplan inlet, different size vortex generators were numerical simulated using Flwent, which can control the boundary separate, improve the totau pressure and swirl distortion.
出处
《航空科学技术》
2015年第4期16-23,共8页
Aeronautical Science & Technology
关键词
S弯进气道
边界层分离
旋流畸变
涡流发生器
数值模拟
s-duct inlet
boundary separate
swirl distortion
vortex generator
numerical simulation
