Abstract
The goal of the paper is to determine the position of the laminar-turbulent transition in subsonic and transonic two-dimensional boundary layers on an airfoil with the use of the a laminar-turbulent transition module based on the eN-method and using the results of numerical simulations of the laminar flow around the model performed by the ANSYS Fluent software. The combined operation of the CFD software and the laminar-turbulent transition module is illustrated by an example of the air flow around the NASA-SR-0410 supercritical airfoil. It is demonstrated that the predicted and experimental data on the laminar-turbulent transition are in good agreement.
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