高马赫数前缘激波-激波干扰  

Shock-shock interactions of high mach leading edge

作　　者：檀姊静 檀妹静 付斌 柳天祥 杨光[2] 闫昊 程响 TAN Zijing;TAN Meijing;FU Bin;LIU Tianxiang;YANG Guang;YAN Hao;CHENG Xiang(School of Civil Engineering,Chang’an University,Xi’an 710061,China;Science and Technology on Space Physics Laboratory,China Academy of Launch Vehicle Technology,Beijing 100076,China)

机构地区：[1]长安大学建筑工程学院,西安710061 [2]中国运载火箭技术研究院空间物理重点实验室,北京100076

出　　处：《航空动力学报》2023年第7期1762-1772,共11页Journal of Aerospace Power

基　　金：中国博士后科学基金(2021M700530)。

摘　　要：采用数值模拟方法及激波极曲线方法开展高马赫数平板-后掠前缘流动结构与热环境特性研究。结果表明:随着后掠角增加,平板斜激波与后掠前缘激波相交,依次形成Ⅳ、Ⅴ、Ⅵ类激波-激波干扰。整体上随着后掠角增加,激波-激波干扰引起的局部压力、热流增量逐渐减小,但过渡型Ⅳ类激波-激波干扰诱导干扰区热流、压力可能低于典型Ⅴ类激波-激波干扰。激波-激波干扰诱导热流随攻角增加而增加,随雷诺数增加而降低。同时,建立了基于临界折转角的高马赫数前缘激波-激波干扰类型判别准则,判别结果经过数值模拟结果验证。形成了高马赫数前缘激波-激波干扰关系、干扰位置及干扰类型图谱,能为高马赫数飞行器总体方案和气动外形设计与优化提供有力支撑。Validated numerical approach and shock polar diagrams method were employed to investigate the flow structure and aerodynamic heating environment around high-mach flat-sweepback leading edge.The results demonstrated that with the increase of sweepback,the flat angle shock and leading edge shock crossed,and thenⅣ,Ⅴ,Ⅵshock-shock interactions were formed in turn.In general,the local pressure and heat flux increment caused by shock-shock interaction decreased with the increase of leading edge,but heat flux and pressure of interference zone under the transitionⅣshock-shock interaction might be lower than that under the typicalⅤshock-shock interaction.Moreover,it was found that the induced heat flux increased with the increase of attack angle,and decreased with the increase of Reynolds number.Also,a convenient discriminant method for high-Mach leading edge shock-shock interaction was provided based on critical deflection angle analysis.The discriminant results were validated against numerical results.The shock-shock interaction relation,interaction location and interference type graph for high-Mach leading edge was presented.The findings could benefit not only high-Mach aircraft integrated design,but also aerodynamic configuration optimization.

关 键 词：激波干扰 流动结构 气动热环境 激波极曲线 干扰类型判别 

分 类 号：V211.745[航空宇航科学与技术—航空宇航推进理论与工程]