HyTRV流场特征与边界层稳定性特征分析  

Characteristics of flow field and boundary-layer stability of HyTRV

作　　者：陈坚强[1,2] 涂国华[1] 万兵兵 袁先旭[1] 杨强[1] 庄宇[3] 向星皓 CHEN Jianqiang;TU Guohua;WAN Bingbing;YUAN Xianxu;YANG Qiang;ZHUANG Yu;XIANG Xinghao(State Key Laboratory of Aerodynamics,China Aerodynamics Research and Development Center,Mianyang 621000,China;Computational Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;Hypervelocity Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心空气动力学国家重点实验室,绵阳621000 [2]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000 [3]中国空气动力研究与发展中心超高速空气动力研究所,绵阳621000

出　　处：《航空学报》2021年第6期253-268,共16页Acta Aeronautica et Astronautica Sinica

基　　金：国家重点研发计划(2016YFA0401200);国家自然科学基金(11772350);国家数值风洞工程。

摘　　要：高超声速转捩研究飞行器(HyTRV)是为研究三维复杂外形的边界层转捩问题而设计的一款具备真实飞行器典型特征的升力体标模。为支撑更加全面系统的理论分析、数值模拟、风洞试验和飞行试验研究,采用高精度数值模拟方法、线性稳定性理论(LST)和eN方法对HyTRV标模的典型流动特征和边界层失稳特征进行了分析。研究表明,HyTRV展现出多个相对独立的横流区域和多个流向涡结构;HyTRV的边界层存在横流失稳模态、第二模态、附着线失稳模态等常见模态。横流失稳模态出现在周向高低压区之间的横流区域,能够主导转捩发生;横流区域同时也存在第二模态,其N值普遍比横流失稳模态小;附着线失稳模态呈现出第二模态特性,且频率非常高。还研究了攻角和单位雷诺数的影响。结果表明,随着攻角增加,标模下表面中心线的流向涡结构逐渐消失,横流雷诺数逐渐减小;上表面流向涡结构逐渐从腰部移向顶端,并出现新的流向涡结构。增加攻角,所有失稳模态的N值总体上逐渐减小;增加单位雷诺数,N值显著增加。基于研究结果,针对流向涡失稳、横流失稳、第二模态和附着线失稳等给出了研究建议。The Hypersonic Transition Research Vehicle(HyTRV)is a lifting body model with typical characteristics of a real aircraft designed for the study of boundary-layer transition on three-dimensional complex geometries.To support a more comprehensive and systematic study of hypersonic transition by means of theoretical analysis,numerical simulations,wind tunnel experiments and flight tests,the typical characteristics of the flow and the boundary-layer instability of the HyTRV model are analyzed with high-order numerical simulation,the Linear Stability Theory(LST)and the eN method.Results show that the HyTRV exhibits several relatively independent crossflow regions and streamwise vortices.The boundary layer of the HyTRV has common typical instability modes such as the crossflow mode,the second mode and the attachment line mode.The crossflow instability mode,which can lead to transition,appears in the crossflow region between the high-and low-pressure zones in the circumferential direction.Meanwhile,the second mode is also found in the crossflow region,though its Nfactor is generally smaller than that of the crossflow instability mode.The attachment line instability mode essentially belongs to the second mode,with a high frequency.The effects of the angle of attack and the unit Reynolds number on the boundary layer transition are also studied.The results show that with the increase of the angle of attack,the streamwise vortex structure along the centerline on the lower surface gradually disappears,and the crossflow Reynolds number gradually decreases;the original streamwise vortices on the upper surface gradually move from the side to the top and new streamwise vortices also appear.The Nfactors of all instability modes in general decrease gradually with the increase of the angle of attack,and increase significantly with the increase of the unit Reynolds number.Based on these results,advice on the typical instabilities including the streamwise vortex instability,the crossflow instability,the second mode and the attachment

关 键 词：升力体 eN方法 横流失稳 附着线失稳 流向涡 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程] V411