Abstract
The steady incompressible inviscid flow past a 3D airfoil with a sharp trailing edge TE is not uniquely determined by the free stream velocity U, unless some information about the shed vorticity is added. Namely, the concentrated vorticity ω normal to TE, which forms the vortex sheet released from the airfoil in steady state conditions, is an extra unknown to be determined by the solution. In fact, the irrotational flow is unique, contrary to what happens in 2D, but the real flow including the wake is not, and a Kutta condition is needed in order to determine ω and to retrieve uniqueness.
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© 1997 Springer Science+Business Media Dordrecht
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Bassanini, P., Casciola, C.M., Lancia, M.R., Piva, R. (1997). On the Removal of the Trailing Edge Singularity in 3D Flows. In: Morino, L., Wendland, W.L. (eds) IABEM Symposium on Boundary Integral Methods for Nonlinear Problems. Springer, Dordrecht. https://doi.org/10.1007/978-94-011-5706-3_1
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DOI: https://doi.org/10.1007/978-94-011-5706-3_1
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