高超声速边界层转捩研究进展与挑战  

Progress and challenges in hypersonic boundary layer transition

作　　者：戴梧叶 孙泓朴 吴宁宁 许灵芝 DAI Wuye;SUN Hongpu;WU Ningning;XU Lingzhi(Beijing Aerospace Technology Institute,China Aerospace Science and Industry Corporation Limited,Beijing 100074,China)

机构地区：[1]中国航天科工集团有限公司北京空天技术研究所,北京100074

出　　处：《航空动力学报》2025年第1期173-188,共16页Journal of Aerospace Power

摘　　要：对风洞试验、飞行试验、e^(N)方法、转捩模式以及转捩准则等常用的高超声速飞行器转捩研究方法及手段进行了介绍,并指出了这些方法在感受性原理以及转捩判据方面的改进。在此基础上,针对压缩拐角、后掠前缘、后掠翼舵面三类典型构型的高超声速转捩特性进行了详细分析,梳理出在Görtler涡增长机理以及横流不稳定性研究方面的关键问题。指出需要在加深转捩机制认知的基础上,提高静音风洞模拟能力与CFD模拟准确度来满足工程对边界层转捩预测的需求。Wind tunnel test,flight experiment,e^(N) method,transition mode and transition criterion were introduced,and the improvements of these methods in the sensitivity principle and transition criterion were pointed out.On this basis,hypersonic transition characteristics of compression corner,swept-back leading edge and swept-back rudder surface were analyzed in detail,and the key problems in Görtler vortex growth mechanism and cross-flow instability research were sorted out.This indicated that on the basis of deepening the understanding of transition mechanism,it is necessary to improve the simulation capability of quiet wind tunnel and the accuracy of CFD simulation to meet the needs of engineering on boundary layer transition prediction.

关 键 词：边界层转捩 高超声速 压缩拐角 后掠前缘 后掠翼舵面 

分 类 号：V211.1[航空宇航科学与技术—航空宇航推进理论与工程]