Aiming at the determination of interference effects due to the wake of the wing, a numerical method has been developed at NLR for too oaloulation of the vortex location behind a thick lifting wing. It may be considered as an extension of too NLR panel method for the determination of the pressure distribution on lifting wing-body combinations in subsonic flow. It comprises an iterative procedure for the determination of the vortex sheet location represented by discrete vortices, for given onset flow conditions. Some features of the method, such as the effect of streamwise stepwise and discretization, have been investigated numerically. A limited comparison has been made with experimental results taken from work in progress at NLR.
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