超声速层流翼自主标模转捩预测及不确定性分析

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 leadingedge 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.