Introduction

The purpose of this tutorial is to compute the turbulent flow past a transonic airfoil at a nonzero angle of attack. You will use the Spalart-Allmaras turbulence model.

This tutorial demonstrates how to do the following:

• Model compressible flow (using the ideal gas law for density).

• Set boundary conditions for external aerodynamics.

• Use the Spalart-Allmaras turbulence model.

• Use Full Multigrid (FMG) initialization to obtain better initial field values.

• Calculate a solution using the pressure-based coupled solver.

• Use force and surface monitors to check solution convergence.

• Check the near-wall mesh resolution by plotting the distribution of $y^+$.