高超声速飞行器自适应减阻盘动态减阻机理  

Dynamic drag reduction mechanism of self-aligned aerodisks on hypersonic aircraft

作　　者：韩荣 刘伟[1] 杨小亮 HAN Rong;LIU Wei;YANG Xiaoliang(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学空天科学学院,长沙410073

出　　处：《航空学报》2023年第4期160-172,共13页Acta Aeronautica et Astronautica Sinica

基　　金：国家重大项目(GJXM92579)。

摘　　要：针对高超声速飞行器在动态机动过程中的减阻问题,基于非定常流动/运动耦合计算方法及动态混合网格生成技术,对自适应减阻盘在高超声速飞行器机动过程中的动态减阻效果开展研究,并分析飞行器阻力特性随不同参数的变化规律,为高超声速飞行器设计及优化提供一定的参考。同时,通过与固定式减阻盘对比,探讨2种方法在减阻机理上的差异。研究发现,在高超声速飞行器机动过程中,自适应减阻盘始终对准来流,有助于维持钝体前方回流区结构,有攻角状态下依然具有流场重构作用。相对于固定式减阻盘,在强迫俯仰振荡过程中,采用自适应方法后,80%以上的时间中减阻效果提升明显;且随着俯仰角增大,自适应方法的优势愈发显著。To address the drag reduction problem of hypersonic aircraft during dynamic maneuver,the dynamic drag reduction effects of self-aligned aerodisks are studied based on the unsteady flow/kinematics coupled method and dy⁃namic hybrid grid generation technique.Drag characteristics of aircraft are also analyzed with variation of different pa⁃rameters to provide reference for hypersonic aircraft design and optimization.In addition,differences in dynamic drag reduction mechanisms between the fixed and self-aligned aerodisks are discussed.The numerical results show that self-aligned aerodisks,always aligning with the incoming flow,are helpful to maintain the structure of recirculation zone during maneuvering.Moreover,self-aligned aerodisks are able to reconstruct the flow field even at a high angle of attack.Compared to that of fixed aerodisks,the drag reduction effect of self-aligned aerodisks can be largely im⁃proved in more than 80%of the oscillation period.Furthermore,the superiority of the self-aligned method clearly in⁃creases with the growing pitch angle.

关 键 词：高超声速飞行器 自适应减阻盘 减阻机理 动态混合网格技术 非定常数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程] O351.2[理学—流体力学] O355[理学—力学]