Poststall prediction of multiple-lifting-surface configurations using a decambering approach

By R. Mukherjee, Ashok Gopalarathnam. 2004

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Discrete-vortex method with novel shedding criterion for unsteady aerofoil flows with intermittent leading-edge vortex shedding (2014, methodology): “The current method can be made more generally applicably by developing a low-order approach for modelling the effect of thick/separated boundary layers, perhaps using a dynamically varying camberline through an adaptation of the decambering approach (Mukherjee & Gopalarathnam 2006).”
Applications of the unsteady vortex-lattice method in aircraft aeroelasticity and flight dynamics (2012, methodology): “Solutions to overcome this have been proposed in the literature, such as semiempirical models for dynamic stall in 2-D aerofoil theory [135, 136], or ad hoc models for the UVLM [8, 145].”