摘要
[目的]翼身组合体是典型的高超声速飞行器构型之一,其独特外形对应的转捩现象及机理对于深入探究复杂外形的边界层转捩具有重要意义.[方法]采用隐式大涡模拟(implicit large eddy simulation,ILES)方法,对一种大翼展翼身组合体外形的边界层转捩现象及机理进行了深入分析.[结果]研究发现,在背/迎风面的机翼上,宽频扰动和角区流向涡展向相干,促使流动发生转捩;在背/迎风面的机身侧缘存在第二模态波,其下游流动同时还受横流效应和角区流动失稳转捩的影响;背风面双锥结构处的膨胀区会抑制不稳定波的振幅进而延迟该区域转捩;迎风面中心线上存在较强的流向涡不稳定性.[结论]在各局部几何结构上多种扰动的作用下,翼身组合体外形呈现由角区起始向下游扩展至机翼和机身,并最终呈三角形分布的转捩特征.这项研究不仅展示了翼身组合体特殊的边界层转捩现象,并揭示了其相关流动机理,也表明了ILES方法在预测高超声速复杂外形边界层转捩问题时的应用潜力,为复杂外形边界层转捩现象及机理的深入研究提供了参考.
[Objective]The wing-body configuration constitutes a typical shape of hypersonic vehicles.Relevant transition phenomena as well as mechanisms associated with its distinctive geometry deserve profound investigations so that the boundary-layer transition of complex shapes can be further understood.[Methods]Herein,employing the implicit large eddy simulation(ILES)method,we conduct thorough simulation analyses of boundary-layer transition phenomena and mechanisms of a wing-body configuration with a large aspect ratio.[Results]The study reveals that,on both leeward and windward surfaces of wings,the broadband disturbance exhibits spanwise interactions with vortices in the corner region,facilitating the transition of the flow.Additionally,second-mode waves occur at the side edges of the fuselage on both surfaces,with the downstream flow also influenced by crossflow effects and the instability-induced transition of the corner region.The expansion region at the leeward double-cone structure suppresses the amplitude of unstable waves,thus delaying the transition in that area.Finally,strong flow vortex instability exists along the centerline of the windward surface.[Conclusions]Under the influence of various disturbances from different local geometric structures,the wing-body configuration exhibits transition characteristics that occur in the corner region,expands the downstream to wings and the fuselage,and eventually forms a triangular distribution.This research not only demonstrates unique boundary-layer transition phenomena of the wing-body configuration and reveals related flow mechanisms,but also highlights the potential application of the ILES method in predicting boundary-layer transition issues for complex hypersonic shapes.Hopefully,it can serve as a guiding reference for further studies on boundary-layer transition phenomena and mechanisms in complex geometries.
作者
周玲
刘国梁
孟庆东
朱慧玲
彭子昂
雷娟棉
ZHOU Ling;LIU Guoliang;MENG Qingdong;ZHU Huiling;PENG Ziang;LEI Juanmian(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China)
出处
《厦门大学学报(自然科学版)》
北大核心
2025年第2期263-276,共14页
Journal of Xiamen University:Natural Science
关键词
高超声速
翼身组合体
边界层转捩
大涡模拟
角区
hypersonic speed
wing-body configuration
boundary layer transition
large eddy simulation
corner region
