Unsteady CFD Analysis of a Delta Wing Fighter Configuration by Delayed Detached Eddy Simulation

Abstract

While the flow physics of generic delta wings with sharp leading edges are largely understood, realistic configurations with rounded leading edges and canards are still of scientific and industrial interest. The goal of the presented study is the investigation of such a realistic delta wing configuration at 15° angle of attack and at high Reynolds number in comparison with detailed wind tunnel measurements. Former studies have shown the superior results of large and Detached-eddy simulations (DES) for delta wings in comparison with RANS computations. The original standard formulation of DES has shown the drawback of only grid based prediction of the boundary layer edge. To overcome this deficiency the technique of Delayed DES (DDES) was developed some years ago. This new model is based on a simple modification of the original formulation to provide a dependency of the RANS-LES switch on turbulent flow properties. The numerical DES and DDES results are compared with data from the TU Munich wind tunnel facility. Comparison of statistical data as well as velocity spectra in the flow field with experiments will be presented.