高超声速旋转钝锥边界层稳定性与转捩研究  

layer flow over a rotating blunt cone SONG DePei1,2,YU ChangPing1,2,3*&Li XinLiang1,2

作　　者：宋德培 于长平 李新亮[1,2] SONG DePei;YU ChangPing;LI XinLiang(State Key Laboratory of High-temperature Gas Dynamics,Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China;School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,China)

机构地区：[1]中国科学院力学研究所,高温气体动力学国家重点实验室,北京100190 [2]中国科学院大学工程科学学院,北京100049

出　　处：《中国科学：物理学、力学、天文学》2024年第10期30-45,共16页Scientia Sinica Physica,Mechanica & Astronomica

基　　金：国家重点研发计划(编号:2020YFA0711801);中国科学院战略性先导科技专项B类(编号:XDB0500301);国家自然科学基金(编号:12072349,12232018,12202457)资助项目。

摘　　要：钝锥体高超声速边界层转捩的预测对于高超声速飞行器的研究具有重要意义,本文通过直接数值模拟研究了流向旋转的钝锥体边界层在高超声速来流中的转捩过程.研究结果表明,随着旋转角速度的提高,转捩起始位置单调地向钝锥头部移动,并且旋转工况下极易发生二次失稳从而导致转捩提前.研究结果还表明旋转工况下边界层中扰动波演化与无旋转工况存在明显差异,并且旋转工况下的模态转换更为丰富.通过频谱分析、谱本征正交分解和动态模态分解技术,揭示了旋转工况下新的高频特征模态的产生.the hypersonic boundary layer transition of a blunt cone is crucial for advancements in hypersonic aircraft research.This work studies the transition process of a blunt cone subjected to a rotating flow direction amid a hypersonic incoming flow using direct numerical simulation.Reportedly,as the rotation angular velocity increases,the transition starting position moves monotonically toward the blunt cone head.Furthermore,under rotation conditions,secondary instability may occur,precipitating an early transition.The evolution of disturbance waves in the boundary layer under rotating conditions differs significantly from that under non-rotating conditions and mode conversion under rotating conditions is rich.Using spectrum analysis and dynamic mode decomposition,we uncovered the generation of new high-frequency characteristic modes under rotating conditions.

关 键 词：高超声速 边界层转捩 直接数值模拟 钝锥 

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