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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