摘要
内外流曲面设计构型的广泛应用对以弯曲激波为特征的激波/边界层干扰机理的认知带来了艰巨挑战,构建全新的弯曲激波/边界层干扰理论体系意义重大。首先基于弯曲激波理论与自由干扰理论构建了二维弯曲入射激波/平板湍流边界层干扰的无黏流动模型,通过将流场划分为弯曲激波/膨胀波干扰区、弯曲激波/分离激波干扰区、边界层流动分离区3个典型流动区域,利用弯曲激波的波后二阶参数实现了对二维弯曲激波/湍流边界层干扰的流场特征描述。随后,采用数值方法验证了该理论模型的精度,在5种不同来流马赫数及激波条件下,分离点、激波交点等各关键坐标最大误差均小于4.5%。在此基础上,利用该模型着重分析了弯曲入射激波强度、边界层厚度、下游扰动对二维弯曲激波/湍流边界层干扰流场的影响规律,总结了分离区上游影响长度的增长特性。该模型是构建三维弯曲激波/边界层干扰理论体系的基础,也为未来弯曲激波/边界层干扰研究提供了一种新手段。
With the wide application of curved compression configurations in internal/external flows,it presents a formidable challenge on perceiving shock wave/boundary layer interactions characterized by curvatures.Thus,to create new theories of Curved Shock Wave/turbulent Boundary Layer Interactions(CSWBLI)is of great importance.In this paper,an inviscid model of 2Dincident curved shock wave/turbulent boundary layer interaction on a flat plate is built based on the curved shock theory and the free interaction theory.The flowfield is divided into three regions:the curved shock wave/expansion wave interaction region,the curved shock wave/separation shock interaction region and the boundary layer region,where the second order parameters behind the curved shock wave are used to describe the characteristics of the 2DCSWBLI flowfield.Thereafter,the accuracy of the model is verified by numerical simulations in five models with different Mach numbers and incident shocks,and the maximum error of the key point such as the separation point and the intersection point is less than 4.5%.Finally,the influences of incident shock,local boundary layer and downstream disturbance on the interaction are analyzed,and the rules of upstream influence length of the separation bubble in the 2DCSWBLI are summarized.The developed model is the fundamental of the flowfield structure of 3DCSWBLI,and also provides a new method for the research on CSWBLI in the future.
作者
程剑锐
施崇广
瞿丽霞
徐悦
尤延铖
朱呈祥
CHENG Jianrui;SHI Chongguang;QU Lixia;XU Yue;YOU Yancheng;ZHU Chengxiang(School of Aerospace Engineering,Xiamen University,Xiamen 361102,China;Chinese Aeronautical Establishment,Beijing 100012,China)
出处
《航空学报》
EI
CAS
CSCD
北大核心
2022年第9期337-349,共13页
Acta Aeronautica et Astronautica Sinica
基金
航空科学基金(2018ZB68008)
技术领域基金(2020-JCJQ-JJ-312)
基础加强项目(PZ2020016)
1912项目。
关键词
弯曲激波
湍流边界层
激波/边界层干扰
流场结构
流动分离
curved shock
turbulent boundary layer
shock wave/boundary layer interaction
flowfield structure
flow separation
