摘要
由于二元混压式进气道的激波/附面层干扰,可能在进气道喉道前形成分离包,导致进气道的无法起动。为了降低进气道的起动马赫数,采取了附面层吸除措施,并运用机理分析、CFD仿真和吹风试验的方法,论述了进气道附面层吸除对进气道起动性能的影响,经过对数值仿真结果和试验数据的对比分析,得出了进气道附面层吸除措施可以降低进气道起动马赫数和提高转级点性能的结论。
Because of shock wave/boundary layer interference of 2D mixed-compression inlet, the separated region was formed and disable the inlet from starting. In order to reduce the inlet start mach number, boundary layer slot-bled was performed, which was analyzed using aerodynamic theory, calculation fluid dynamic simulation and wind tunnel experiment. The comparison between simulation reswt and exptest data shows that the inlet performacecan influence rules of bleed sew, and is confirmed to be efficient for inlet start.
出处
《弹箭与制导学报》
CSCD
北大核心
2009年第3期149-152,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
进气道
吸除槽
起动
激波
附面层
干扰
airinlet
bleed sew
start
shockwave
boundary layer
interference
