Comparative scale-resolving and rans simulations of a delta wing configuration

The vortex dominated flow around the triple-delta wing aircraft model ADS-NA2-W1 is investigated comparing RANS with scale-resolving DDES results. The Spalart-Allmaras One-Equation Model with corrections for negative turbulent viscosity and Rotation/Curvature (SA-negRC) is employed to close the RANS equations, whereas in the scale-resolving computations the SA-based DDES model is applied. The TAU-Code solver developed by the German Aerospace Center (DLR) is employed in order to perform the numerical simulations. The solutions achieved in the current work are compared with the experimental data provided by Airbus Defence and Space. The aim is a better understanding of the vortex-dominated flows particularly in the transonic speed range in order to determine the range of the suitability of current CFD methods.