Abstract
SummaryAn economic numerical method has been developed to calculate the incompressible potential flow about complete aircraft configurations by taking advantage of the computational efficiency of the internal distribution of singularities. For wing and wing-like components, source and vorticity singularities are distributed on the respective mean camber surfaces, while the fuselage carries a source distribution on its wetted surface. The singularity strengths are obtained by satisfying the flow tangency condition at selected points on all the wetted surfaces of the configuration. No attempt has been made to consider wing or body vortex shedding or separation. The results of the present method were compared with other theoretical and experimental data.
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