A Dynamic Stall Model for Airfoils with Deformable Trailing Edges

The present work contains an extension of the Beddoes-Leishman-type dynamic stall model. In this work, a deformable trailing-edge flap has been added to the dynamic stall model. The model predicts the unsteady aerodynamic forces and moments on an airfoil section undergoing arbitrary motion in heave, lead-log, pitch, trailing-edge flopping. In the linear region, the model reduces to the inviscid model, which includes the aerodynamic effect of a thin airfoil with a deformable camberline in inviscid flow. Therefore, the proposed model can be considered a crossover between the work of Gaunaa for the attached flow region and Hansen et al. The model is compared qualitatively to wind tunnel measurements of a RisoB1-18 blade section equipped with deformable trailing-edge flap devices in the form of piezoelectric devices. Copyright (C) 2009 John Wiley & Sons, Ltd.