Delta wing configurations are commonly employed for high agility supersonic aircraft and aerodynamic devices such as vortex generators, and have thus been a focus of extensive investigations over the past decades.

We performed wall modeled large eddy simulation of the flow field around a delta wing with sweep angle of 65 ∘ and round leading edge at angles of attack of 13∘ , 18 ∘ , and 23 ∘ . Qualitatively, the numerical simulations correctly predict the flow phenomena for all angles of attack considered. Quantitatively, the results show reasonable agreement with experimental measurements of steady and unsteady surface pressures, velocity distributions, and vortex breakdown position and frequency