Jose I. Rothkegel, Grigorios Dimitriadis

DOI Number: N/A

Conference number: IFASD-2015-011

An interactive boundary layer model has been developed in 2D in order to solve the unsteady flow around an airfoil. The inviscid problem is solved using a panel method, by the discretization of the airfoil into linear-varying vortex panels. The solution of the boundary layer equations is carried out using a finite volume scheme. Viscousinviscid coupling is preformed by imposing a permeation velocity on the skin panels of the airfoil and the addition of a free wake at each separation point.

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In Categories: 2. IFASD 2015, Aerodynamics/CFD
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