超声速层流翼自主标模转捩预测及不确定性分析

doi:10.7527/S1000-6893.2025.31923

Abstract

Abstract:

Laminar flow drag reduction is one of the key technologies for enhancing the comprehensive performance of supersonic civil aircraft. However， further research is required in its engineering application， particularly regarding the calibration of transition prediction models for supersonic laminar wings and their sensitivity to external disturbances. In this paper， two self-developed benchmark models of supersonic laminar wing are designed， one with a supersonic leading edge and the other with a subsonic leading edge. Wind tunnel test results demonstrated that the supersonic leading-edge laminar wing maintained a laminar region of 30%c to 60%c， while the subsonic leading-edge laminar wing exhibited laminar regions spanning approximately 20%c to 70%c. Experimental and numerical analysis confirmed that the e^N transition prediction method， based on linear stability theory， accurately captured the transition phenomena of supersonic laminar wings， with a calibrated critical N factor of 5.2. Furthermore， the self-adaptive Kriging method was developed to quantify the impact of high-dimensional， multi-source uncertainties， including critical N factor， operating conditions， and geometry deviation on transition prediction. Uncertainty quantification analysis reveals substantial variation in the influence degree of uncertainty factors on the performance metrics of different supersonic laminar wing benchmark models. The critical N factor has the greatest influence on transition prediction for the supersonic leading-edge laminar model. For the subsonic leading-edge laminar model， Mach number disturbances have the most significant impact on transition prediction. The self-developed benchmark models for supersonic laminar wings designed in this paper， along with the calibrated critical N factor and revealed uncertainty influence mechanisms， are of significant importance for achieving precise transition prediction and aerodynamic robust design optimization for supersonic laminar wings.

Key words: supersonic laminar wings, self-developed benchmark models, transition prediction, adaptive Kriging, uncertainty analysis, transition critical

CLC Number:

V221.3

Yayun SHI, Xinze JI, Tihao YANG, Pengfei WU, Lu XIE, Junqiang BAI, Kaixuan FENG. Transition prediction and uncertainty analysis of self-developed benchmark models for supersonic laminar wings[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(20): 531923.

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序号	后掠角/（°）	攻角/（°）	马赫数	雷诺数/10⁶
1	30	0.0	1.6	8.0
2	30	2.0	1.6	8.0
3	60	2.0	1.9	4.0
4	60	2.5	1.9	4.0
5	60	0.0	1.9	8.0

后掠角/（°）	展向站位	马赫数	转捩区长/当地弦长
30	40%	1.6	0.399 0
	50%	1.6	0.456 0
	60%	1.6	0.490 4
60	50%	1.9	0.198 5
	60%	1.9	0.215 8
	70%	1.9	0.220 2

后掠角/（°）	展向站位	马赫数	转捩位置期望	转捩位置标准差
30	40%	1.6	0.370 1	0.036 5
	50%	1.6	0.420 4	0.040 2
	60%	1.6	0.452 1	0.039 3
60	50%	1.9	0.216 2	0.041 5
	60%	1.9	0.235 6	0.044 3
	70%	1.9	0.236 9	0.038 4

Transition prediction and uncertainty analysis of self-developed benchmark models for supersonic laminar wings

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References 45

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序号	后掠角/（°）	攻角/（°）	马赫数	雷诺数/10⁶
1	30	0.0	1.6	8.0
2	30	2.0	1.6	8.0
3	60	2.0	1.9	4.0
4	60	2.5	1.9	4.0
5	60	0.0	1.9	8.0

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序号	后掠角/（°）	攻角/（°）	马赫数	雷诺数/10⁶
1	30	0.0	1.6	8.0
2	30	2.0	1.6	8.0
3	60	2.0	1.9	4.0
4	60	2.5	1.9	4.0
5	60	0.0	1.9	8.0

序号	后掠角/（°）	攻角/（°）	马赫数	雷诺数/10⁶
1	30	0.0	1.6	8.0
2	30	2.0	1.6	8.0
3	60	2.0	1.9	4.0
4	60	2.5	1.9	4.0
5	60	0.0	1.9	8.0