Recent developments in high-fidelity CFD analyses of dynamic stall on three-dimensional, rotating systems has disrupted the classic view of dynamic stall. Visual inspection of rich flowfields generated from these studies lead research and academia subject matter experts to observe that in addition to rigid and elastic blade motion, dynamic stall may be triggered by other mechanisms, such as blade-vortex interactions, tip shocks, fluid structure coupling, and other complex phenomena associated with rotorcraft aeromechanics. The UH-60A four-bladed, articulated rotor was studied at various test points from the 2010 National Full-Scale Aerodynamics Complex (NFAC) 40-by-80 foot wind tunnel test. Four-bladed, loosely-coupled CFD-CSD predictions were compared to one-bladed predictions using prescribed motion to isolate the effects of blade motion from the effects of complex aerodynamics associated with blade-vortex interactions (BVI) associated with dynamic stall. From these, further insights into the role of BVI on rotor blade separation and the onset of dynamic stall.
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