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. The analysis will be conducted for a generic double and triple delta wing configuration, for which numerical data based on the enhanced turbulence model will be compared to results for the original turbulence model and high-fidelity datasets based on delayed-detached-eddy simulations as well as experimental data such as aerodynamic coefficient polars and particle image velocimetry results © 2024, International Council of the Aeronautical Sciences. All rights reserved.     «

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 Ma...     »