On predicting the onset of the transition to turbulence in the three-dimensional boundary layer on a swept wing.

The results of numerical simulation of a subsonic flow around a 45-degree swept wing model with a NACA 67 1-215 airfoil are considered. The simulation was performed using the ANSYS Fluent package with a plug-in original module LOTRAN for predicting the position of laminar-turbulent transition, which implements the eN-method. In particular, the distributions of N-factors for the instability to Tollmien – Schlichting waves and crossflow vortices at different free-stream velocities are presented. A comparison of these distributions with the experimental data obtained in the wind tunnel T-324 of the ITAM SB RAS for the position of the transition is demonstrated. [ABSTRACT FROM AUTHOR]