Abstract:
Accurate modeling of rotorcraft aerodynamics and induced flow fields is important for high fidelity flight dynamics simulation and pilot training applications. A real-time, free-wake rotor induced velocity software module has been developed and integrated with a Navy helicopter flight dynamics simulation for testing in multiple pilot evaluations. The model provides a physically-based approach for simulation of rotorcraft aerodynamic phenomena identified by strong vortex wake interactional effects. Such phenomena include wake interactions between the main rotor, tail rotor, fuselage and empennage; vertical descent through vortex ring state; and rotor wake/ship air wake interactions. This paper provides an overview of the wake model and flight dynamics simulation integration. Comparison of the coupled free wake aerodynamics and flight dynamics model with flight test data for an MH-60S helicopter was performed, focusing on vertical descent and shipboard operations. A summary of findings from pilot evaluations within the NAVAIR Manned Flight Simulator facility is also given.