Prediction of Airfoil Stall Based on a Modified {formula-present} Turbulence Model

Abstract

The accuracy of an airfoil stall prediction heavily depends on the computation of the separated shear layer. Capturing the strong non-equilibrium turbulence in the shear layer is crucial for the accuracy of a stall prediction. In this paper, different Reynolds-averaged Navier–Stokes turbulence models are adopted and compared for airfoil stall prediction. The results show that the separated shear layer fixed {formula-present} (abbreviated as SPF{formula-present}) turbulence model captures the non-equilibrium turbulence in the separated shear layer well and gives satisfactory predictions of both thin-airfoil stall and trailing-edge stall. At small Reynolds numbers {formula-present}, the relative error between the predicted CL,max of NACA64A010 by the SPF {formula-present} model and the experimental data is less than 3.5%. At high Reynolds numbers {formula-present}, the Cp,max of NACA64A010 and NACA64A006 predicted by the SPF {formula-present} model also has an error of less than 5.5% relative to the experimental data. The stall of the NACA0012 airfoil, which features trailing-edge stall, is also computed by the SPF {formula-present} model. The SPF {formula-present} model is also applied to a NACA0012 airfoil, which features trailing-edge stall and an error of CL relative to the experiment at CL > 1.0 is smaller than 3.5%. The SPF {formula-present} model shows higher accuracy than other turbulence models.