基于C-γ-Reθ 模型的多模态高超声速边界层转捩预测

doi:10.7527/S1000-6893.2023.29215

Abstract

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-Re_θ transition model based on the original γ-Re_θ transition model. In this study， the C-γ-Re_θ 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-Re_θ 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-Re_θ 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-Re_θ 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-Re_θ 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:

V211.3

Zhenyu HU, Fengshou XIAO, Jianqiang CHEN, Xianxu YUAN, Yifeng ZHANG, Xinghao XIANG. Prediction of multi-mode hypersonic boundary layer transition based on C-γ-Re_θ model[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(12): 129215-129215.

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工况	湍流度 Tu/%	粗糙度 h/μm	马赫数 Ma	单位雷诺数 Re/（10⁶ m^-1）	飞行高度 H_p/m
1	0.1	2	7.70	5.0	26.36
2			7.73	6.0	25.24
3			7.77	8.0	23.48
4			7.82	10.0	22.14
5			7.85	12.0	21.05
6			7.87	14.0	20.12
7			7.90	17.0	18.91
8			7.85	20.0	17.84

工况	湍流度 Tu/%	粗糙度 h/μm	单位雷诺数Re/（10⁷ m^-1）	马赫数 Ma
1	4.0	1.6	0.46	6
2	4.0	1.6	0.98	6
3	4.0	1.6	2.38	6
4	4.0	1.6	0.99	5
5	4.0	1.6	1.04	7
6	4.0	1.6	0.99	8

工况	X_model/m	X_Exp/m^［32］	ΔX/%
1	0.66	0.80	16.26
2	0.57	0.60	3.48
3	0.44	0.45	1.16
4	0.37	0.35	2.32
5	0.32	0.35	3.48
6	0.28	0.30	2.32
7	0.25	0.30	5.81
8	0.22	0.30	9.29

Ma	X_Exp/m	X_e_N /m	X_model/m	ΔX/%
5	0.48	0.44	0.48	0.00
6	0.56	0.52	0.54	2.50
7	0.64	0.62	0.60	5.00
8	0.71	0.70	0.69	2.50

Ma	X_Exp/m	X_e_N /m	X_model/m	ΔX/%
5	0.46	0.44	0.64	22.50
6	0.55	0.52	0.54	1.25
7	0.62	0.60	0.55	8.75
8	0.64	0.60	0.58	7.50

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

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

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