ASSESSMENT OF AN ADAPTIVE ONE-EQUATION TURBULENCE MODEL FOR LEADING EDGE VORTEX FLOWS ON MULTIPLE SWEPT DELTA WINGS

Eddy-viscosity turbulence models based on the Boussinesq assumption provide the baseline model for computational fluid dynamics simulations of aerospace applications. In the leading edge vortex flow of high-agility aircraft of mid to low-aspect-ratio wings, these models show a deficit in accuracy, where the deviations from real-world flow fields originate in turbulence modeling. Just the possible combinations of angle of attack, angle of sideslip, and control surface deflections at a distinct Mach number call for an enormous amount of computational fluid dynamics simulations in the aircraft design phase. Thus, employing scale-resolving techniques or using more complex turbulence models is not feasible. This study delivers a detailed analysis of an adaptive turbulence model based on the one equation Spalart-Allmaras turbulence model, designed with special emphasis on leading edge vortex flows.