Higher-Order Accurate Computations of Maneuvering Unmanned Combat Air Vehicle Configurations

In this paper a well-validated and robust high-order technique is used to solve the unsteady, three-dimensional Navier-Stokes equations for a 50.. sweep delta wing undergoing dynamic motion. A higher-order overset mesh technique is used to represent complex geometric details and accomplish efficient parallel implementation via a domain decomposition approach. A novel hybrid RANS/ILES approach is investigated for modeling the massively separated, turbulent flows over this low sweep wing. Initial computations for a constant rate pitching motion and a sinusoidally oscillating plunging motion are performed. Vortex reformation is demonstrated as a result of the sinusoidal plunging motion.