Universal Wall Functions for Aerodynamic Flows: Turbulence Model Consistent Design, Potential and Limitations

Abstract

A universal wall-function method for RANS turbulence modelling is presented which allows for a considerable solver accelaration and reduction of memory consumptions at only a small loss in accuracy even in flows with separation and reattachment. The range of validity of the approach in investigated by considering the near-wall RANS solutions in regions of strong adverse pressure gradient leading to separation and near stagnation points. The method is then applied successfully to aerodynamic flows with separation including transonic flows with shock induced separation and a subsonic highlift airfoil close to stall. From this some first best practice guidelines are suggested.