27th Congress of International Council of the Aeronautical Sciences, 19 - 24 September 2010, Nice, France
Paper ICAS 2010-2.2.1

STUDY OF AN EDGE-BASED FINITE VOLUME SCHEME AT WING TRAILING EDGE AND THE INFLUENCE ON THE OVERALL ACCURACY

L. Tysell
FOI, Sweden

Keywords: inviscid computations, grid generation, accuracy,wing trailing edge

It is shown the common implementation of the boundary conditions for an edge-based flow solver at the trailing edge of a wing may have a non-negligible effect on lift and drag. This cause the accuracy order to be less than two, preventing extrapolations of solutions to infinite grid resolution.

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