NUMERICAL STUDY OF FLOW AFTER NASA 0012 AERODYNAMIC PROFILE BASED ON THE SST TURBULENCE MODEL

The article presents a study of the SST turbulence model in the Comsol Multiphysics software package for the problem of subsonic flow around a NACA0012 profile with angles of attack from 0 to 15 degrees, respectively. In this work, the finite element method is used for the numerical implementation of the turbulence equations. To stabilize the discretized equations, stabilization using the Galerkin least squares method was used. The results obtained are compared with the results of experimental data. The results showed good convergence of the SST turbulence model with experimental data.

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