Numerical simulation of flow past NACA0012 airfoil at different angle of attack using spalart–allmaras turbulence model.

The present work represents a study on the effectiveness of Spalart – Allmaras turbulence model using NACA0012 airfoil by comparing its result with reference results published by NASA research center. The NACA0012 airfoil (2D) is modeled using standard coordinates. The grid independent meshed model of the airfoil is analyzed for Re = 6 x 106 with different identical angle of attack under standard boundary conditions using ANSYS Fluent. The drag and lift force coefficients have been calculated and compared with reference results that show a close match. That supports the effectiveness of S-A model based solvers to handle similar aerodynamics problems. [ABSTRACT FROM AUTHOR]