航空学报2025，Vol.46Issue(20)：129-145,17.DOI:10.7527/S1000-6893.2025.31923
超声速层流翼自主标模转捩预测及不确定性分析
Transition prediction and uncertainty analysis of self-developed benchmark models for supersonic laminar wings
史亚云 1季昕泽 2杨体浩 2吴鹏飞 2谢露 3白俊强 4冯凯旋1
作者信息
- 1. 西安交通大学 航天航空学院,西安 710049||复杂服役环境重大装备结构强度与寿命全国重点实验室,西安 710049
- 2. 西北工业大学 航空学院,西安 710072||飞行器基础布局全国重点实验室,西安 710072
- 3. 航空工业第一飞机设计研究院,西安 710089
- 4. 西北工业大学 无人系统研究院,西安 710072||无人飞行器技术全国重点实验室,西安 710072
- 折叠
摘要
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 eN 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,oper-ating 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 signifi-cant 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 lami-nar wings.关键词
超声速层流翼/自主标模/转捩预测/自适应Kriging/不确定性分析/转捩阈值Key words
supersonic laminar wings/self-developed benchmark models/transition prediction/adaptive Kriging/uncertainty analysis/transition critical分类
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史亚云,季昕泽,杨体浩,吴鹏飞,谢露,白俊强,冯凯旋..超声速层流翼自主标模转捩预测及不确定性分析[J].航空学报,2025,46(20):129-145,17.
