Assessment of Turbulence Models for Unsteady Separated Flows Past an Oscillating NACA 0015 Airfoil in Deep Stall

This paper provides 2D Computational Fluid Dynamics (CFD) investigations, using OpenFOAM package, of the unsteady separated fully turbulent flows past a NACA 0015 airfoil undergoing sinusoidal pitching motion about its quarter-chord axis in deep stall regime at reduced frequency 0.1, free stream Mach number 0.278, and Reynolds number, based on chord length, , . First, eighteen steady-state computations coupled with SST model were carried out various angles attack to investigate static stall. Then, Unsteady Reynolds-Averaged Navier-Stokes (URANS) simulations flow around oscillating out. Three eddy viscosity turbulence models, namely Spalart-Allmaras, Launder-Sharma considered for closure. The results are compared experimental data where boundary layer has been tripped airfoil’s leading-edge. findings suggest that performs best among other two models predict aerodynamic forces main features characteristic regime. influence moving downstream mid was also investigated URANS model. It found this induces higher peaks nose-down moment delays onset. However, qualitative behavior post-stall remains unchanged. details development associated dynamic discussed