空气动力学学报2018，Vol.36Issue(2)：196-212,17.DOI:10.7638/kqdlxxb-2018.0017
高超声速边界层转捩实验综述
Boundary-layer transition experiments in hypersonic flow
摘要
Abstract
Laminar/turbulent boundary-layer transition has a large impact on the viscous coefficient and the heat flux,which are critical for aerodynamic and thermal protection design of hypersonic vehicles.Due to the complexity of hypersonic flow and the numerous factors affecting transition,the mechanism of hypersonic laminar/turbulent boundary-layer transition is still outstanding despite the research upon this issue has been lasting for more than half a century,prohibiting the design of advanced hypersonic vehicles.Ground wind tunnel experiment acts as a significant approach in hypersonic aerodynamic design and is expected to play an important role in the research of hypersonic boundary-layer transition in the future.Based on the hypersonic boundary-layer instability and transition experiments in wind tunnel,the receptivity and linear phases were respectively reviewed according the process of natural transition.Discussions and suggestions were given for experimental study of hypersonic boundary-layer transition.关键词
高超声速流动/边界层转捩/感受性/稳定性/实验测量技术/转捩测量Key words
hypersonic flow/boundary-layer transition/receptivity/stability/experimental method/transition measurement分类
数理科学引用本文复制引用
刘向宏,赖光伟,吴杰..高超声速边界层转捩实验综述[J].空气动力学学报,2018,36(2):196-212,17.基金项目
国家自然基金青年科学基金项目(11702106) （11702106）
装备预先研究项目(1406020901) （1406020901）
