A boundary layer transition prediction method based on three-dimensional flowfield for complex high-Mach vehicles

Boundary layer transition of high - Mach vehicles is an inevitable flow phenomenon during flight. It significantly impacts the vehicle's aerodynamic performance and thermal characteristics. The aerodynamic shape of advanced high-Mach vehicle is very complex, leading to distinct three-dimensional flow characteristic. In this work, an applicable method based on three-dimensional flowfield is developed to predict the transition by identifying the boundary layer characteristic parameters. The influence of various flight parameters on the boundary layer transition has been analyzed. It is demonstrated that the developed method can accurately predict the boundary layer transition induced by streamwise and crossflow instability. This is of great significance for enhancing the thermodynamic design and minimizing risks during flight tests.