航空学报 > 2021, Vol. 42 Issue (9): 625711-625711   doi: 10.7527/S1000-6893.2021.25711

国家数值风洞(NNW)进展及应用专栏

C-γ-Reθ高超声速三维边界层转捩预测模型

向星皓1, 张毅锋1, 袁先旭1, 涂国华1, 万兵兵1, 陈坚强1,2   

  1. 1. 中国空气动力研究与发展中心 空气动力学国家重点实验室, 绵阳 621000;
    2. 中国空气动力研究与发展中心 计算空气动力研究所, 绵阳 621000
  • 收稿日期:2021-03-30 修回日期:2021-04-23 发布日期:2021-05-10
  • 通讯作者: 陈坚强 E-mail:chenjq@cardc.cn
  • 基金资助:
    国家重点研发计划(2016YFA0401200);国家数值风洞工程;国家自然科学基金(11872370,12002355)

C-γ-Reθ model for hypersonic three-dimensional boundary layer transition prediction

XIANG Xinghao1, ZHANG Yifeng1, YUAN Xianxu1, TU Guohua1, WAN Bingbing1, CHEN Jianqiang1,2   

  1. 1. State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China;
    2. Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
  • Received:2021-03-30 Revised:2021-04-23 Published:2021-05-10
  • Supported by:
    National Key Research and Development Program of China (2016YFA0401200); National Numerical Windtunnel Project; National Natural Science Foundation of China (11872370, 12002355)

摘要: 针对国家数值风洞(NNW)工程高超声速三维边界层转捩预测需求,开展了高超声速边界层横流转捩判据及模型研究。采用线性稳定性分析eN方法对高超声速转捩数据进行扩展,结合横流强度与表面粗糙度构造当地化的高超声速横流转捩判据,对基于Chant 2.0计算平台的高超声速修正γ-Reθ转捩模型进行了横流模式拓展,建立了适用于高超声速三维边界层横流转捩预测的C-γ-Reθ转捩模型。采用构建的转捩模型对多状态下的高超声速尖锥进行横流转捩预测,取得了与试验结果符合较好的预测效果。

关键词: 国家数值风洞工程, 高超声速流动, 三维边界层, 横流转捩, 转捩模型

Abstract: To meet the need for hypersonic three-dimensional boundary layer transition prediction for the National Numerical Windtunnel (NNW) Project, we study the hypersonic cross-flow transition criterion and the transition model. The hypersonic database is expanded using the linear stability theory of the eN method, a fully-localized hypersonic cross-flow transition criterion constructed combining the cross flow strength and surface roughness, a cross-flow extension of the hypersonic modified γ-Reθ transition model conducted based on the Chant 2.0 computing platform, and a C-γ-Reθ transition model suitable for hypersonic 3D boundary layer transition prediction established. The transition model is used to predict the cross-flow transition on hypersonic sharp cones in multiple states, and the predicted results are in good accordance with the experimental results.

Key words: National Numerical Windtunnel Project, hypersonic flow, 3D boundary layer, cross-flow transition, transition model

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