Publication Details
Beckett Y. Zhou, Nicolas R. Gauger, Christos Tsolakis, Juliette Pardue, Andrey Chernikov, Fotios Drakopoulos, Nikos Chrisochoides and Boris Diskin.
In AIAA Aviation Forum 2019, Dallas, June, 2019
Abstract
Hybrid RANS-LES computations are performed for the turbulent flow around a delta wing at a low sub- sonic Mach number M∞ = 0.07 and an angle of attack of 23◦ . An automated mesh generation methodology is used to generate a mixed-element mesh around the delta wing with a sharp leading edge and a leading- edge sweep angle of 65◦ . The delayed detached eddy simulation with shear-layer adapted (SLA) subgrid scale model in the SU2 open-source solver suite has been applied to predict the vortex breakdown phenomenon that is known to occur at these flow conditions. Three meshes of increasing density are considered. Mean pressure distribution, resolved turbulence kinetic energy and mean axial velocity distribution obtained from the simu- lations are compared with experimental data. It is clear from current results that a fine mesh adapted to the essential flow physics in leading edge and the vortex core regions is necessary to better capture the shear layer instability and vortex breakdown phenomenon.
