An interactive boundary-layer method is described for computing unsteady incompressible flows over airfoils, including the initiation of dynamic stall. The inviscid unsteady panel method developed by Platzer and Teng is extended to include viscous effects. The solutions of the boundary-layer equations are obtained with an inverse finite-difference method employing an interaction law based on the Hilbert integral, and the algebraic eddy-viscosity formulation of Cebeci and Smith. The method is applied to airfoils subject to periodic and ramp-type motions and its abilities are examined for a range of angles of attack, reduced frequency, and pitch rate.
An Inviscid-Viscous Interaction Approach to the Calculation of Dynamic Stall Initiation on Airfoils
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Cebeci, T., Platzer, M. F., Jang, H. M., and Chen, H. H. (October 1, 1993). "An Inviscid-Viscous Interaction Approach to the Calculation of Dynamic Stall Initiation on Airfoils." ASME. J. Turbomach. October 1993; 115(4): 714–723. https://doi.org/10.1115/1.2929307
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