Comparison of Reynolds-Averaged Navier-Stokes Simulations of Multi-Element High-Lift Configurations

Abstract

In this study, flow computations are performed on three-dimensional high-lift configurations on multiblock structured and unstructured meshes with two turbulence models, Spalart-Allmaras model and Menter's shear stress transport model. Two kinds of three-element trapezoidal wings with full-span flap or part-span flap are computed. The objectives of this paper are to investigate the mesh dependency and the effect of turbulence models and improve the reliability in simulating the flow around high-lift devices. Importance of the mesh resolution to resolve the separated corner flows near the wing-fuselage junction is shown to improve the accuracy of computational results. It is also shown that the maximum lift and the angle at which it occurs are very sensitive to turbulence model and Menter's model gives better results at a higher angle of attack in the present computations. Nomenclature AR= aspect ratio of the wingsurface pressure coefficient c = mean aerodynamic chord e = Oswald efficiency factor M 1 = freestream Mach number Re = Reynolds number = angle of attack

Turbulent Flow Simulations on Unstructured Grids using a Reynolds Stress Model

“…Results show that lack of far field boundary resolution may result in a significant loss of accuracy, especially in the prediction of the pressure drag. 26 …”