| Citation: | LI Changlin, TONG Xin, YU Peixiang, et al. New method for predicting the transition position of airfoil surface based on XGBoost model[J]. Journal of Aerospace Power, 2024, 39（11）：20220210 doi: 10.13224/j.cnki.jasp.20220210
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For identification of the transition position on the blade surface, a turbulence/non-turbulence interface identification method based on XGBoost model without specified thresholds was introduced. According to this method, the high-precision flow field around the controlled diffusion airfoil was solved by the large eddy simulation method. Considering the intermittent flow, the proportions of laminar flow state at different positions in the boundary layer at different times were calculated by the machine learning method, and the transition position was obtained according to the change rate in the chord length direction of the airfoil. The method was verified by investigating different influencing parameters. Compared with traditional criteria, this method could accurately predict transition positions without subjective judgment. In addition, using the present method, it was found that for a controlled diffusion airfoil, the boundary layer transition depended not only on the turbulent energy, but also on the size of vortices and the space distribution feature.
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