摘要
以二维高超声速进气道GK01为计算模型,对进气道进行无粘、粘性以及边界层分离控制方法数值研究。结果发现,利用文中设计的壁面开缝措施可以有效减小甚至消除激波/边界层干扰带来的边界层分离现象,降低粘性效应造成的负面影响;相对开缝前,开缝措施在设计点和非设计点均能明显提高进气道的总压恢复系数和动能效率,而对流量捕获系数的影响很小。同时文中给出了开缝措施在非设计点下对进气道性能指标的影响规律。
Taking 2-D hypersonic inlet GK01 as the computational model,inviscid and viscous calculations,as well as boundary layer separation control method on the inlet were numerically studied.The results showed that,the measure of slotting designed in the paper can effectively reduce or even eliminate the boundary layer separation phenomenon induced by shock / boundary layer interaction and decrease the negative effects of viscous effects.Before adopting measure relatively,the slotting can significantly improve the inlet total pressure recovery coefficient and kinetic energy efficiency at design and off-design point,while has little effect on mass capture coefficient.Meanwhile,the effect of slotting on the inlet＇s performance index at the off-design point is given in this paper.
出处
《空气动力学学报》
EI
CSCD
北大核心
2011年第1期68-72,共5页
Acta Aerodynamica Sinica
基金
国防基础科研项目
国家自然科学基金(10572115)
关键词
高超声速进气道
边界层分离
开缝
总压恢复系数
hypersonic inlet
boundary layer separation
slotted
total pressure recovery coefficient
