摘要
针对超燃冲压发动机进气道由于激波-边界层干扰引起的边界层分离以及进气道堵塞问题,提出了一种基于Tollmien-Schlichting(T-S)波谐频共振原理的进气道边界层控制方法,并通过一种典型的二元进气道风洞试验进行了方法验证.研究结果表明,提出的转捩控制方法能够较好地消除由激波-边界层干扰而引起的边界层分离现象,进而降低边界层分离对进气道性能的不良影响,确保进气道性能.同时说明,在超燃进气道设计过程中,需要充分考虑边界层转捩问题,引入有效的边界层转捩控制方法,以保证发动机的正常工作.
For the boundary separation and blockage of the scramjet inlet by the shock wave and boundary interaction,a kind of boundary control method based on Tollmien-Schlichting（T-S） wave syntony principle was presented,and the method was validated by the wind tunnel test for a typical two-dimensional inlet.The results of the example show that the boundary control method could eliminate the boundary separation efficiently,and decrease the negative influence of boundary separation,thereby maintaining the inlet＇s capability.Meanwhile,the research shows that the boundary transition should be considered,and effective transition method should be adopted to ensure normal work of the scramjet engine.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第11期2420-2424,共5页
Journal of Aerospace Power
基金
武器装备预研基金(9140A1302)
