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Acta Aeronautica et Astronautica Sinica ›› 2024, Vol. 45 ›› Issue (12): 129215-129215.doi: 10.7527/S1000-6893.2023.29215

• Fluid Mechanics and Flight Mechanics • Previous Articles    

Prediction of multi-mode hypersonic boundary layer transition based on C-γ-Reθ model

Zhenyu HU1, Fengshou XIAO2, Jianqiang CHEN1,3, Xianxu YUAN1,3, Yifeng ZHANG3, Xinghao XIANG1()   

  1. 1.State Key Laboratory of Aerodynamics,Mianyang  621000,China
    2.Beijing System Design Institute of Electro-mechanic Engineering,Beijing  100039,China
    3.Computational Aerodynamic Institute China Aerodynamics Research and Development Center,Mianyang  621000,China
  • Received:2023-06-25 Revised:2023-07-18 Accepted:2023-08-07 Online:2023-12-15 Published:2023-08-18
  • Contact: Xinghao XIANG E-mail:kinog67@163.com
  • Supported by:
    National Key R & D Program of China(2019YFA0405204);National Natural Science Foundation of China(92052301);Foundation of State Key Laboratory of Aerodynamics(JBKYC190110)

Abstract:

Standard models such as HIFiRE-5 and HyTRV are used in the validation of hypersonic three-dimensional boundary layer transition. Hypersonic crossflow transition correction is proposed in the C-γ-Reθ transition model based on the original γ-Reθ transition model. In this study, the C-γ-Reθ transition model is applied to transition simulation of HIFiRE-5 and HyTRV under flight test and wind tunnel test conditions. For the flight test of HIFiRE-5, transition prediction is conducted under the conditions including eight typical altitudes and one attitude angle, the results of the C-γ-Reθ transition model are consistent with the heat-flux measurements, and the transition modes on the surface of HIFiRE-5 are compared. For the quiet/noise wind tunnel test of HIFiRE-5, the C-γ-Reθ transition model can accurately calculate the transition front shape and the transition onset location, and the results coincide with the temperature difference measurements. For the noise wind tunnel test of HyTRV, the C-γ-Reθ transition model calculation results of the upper and lower surfaces match with the infrared thermogram measurements under the conditions involving various Reynolds numbers and Mach numbers, and the ability to predict boundary layer transition in the crossflow mode is verified. Its prediction precision of the transition onset location and the transition front shape is on par with the e N method based on LST. As shown in the numerical simulation results, for each of the flight test and the quiet/noise wind tunnel test, the C-γ-Reθ transition model maintains high prediction reliability, and has achieved hypersonic three-dimensional boundary layer transition prediction for typical standard models.

Key words: transition model, crossflow correction, hypersonic correction, three-dimensional boundary layer, transition mode

CLC Number: