Abstract
A performance calculation method for multielement airfoil sections with separation is described in this paper. The potential flow analysis is based on a distributed-singularity method which uses linear-vortex and constant-source distributions. The wake is replaced by source flow representing its displacement effect. The strength of souce is given by an experimental relation derived from tangential directions at separation point. The circulation about each airfoil is determined by conditions of upper and lower separation points. The flow inside the separated streamlines is ignored and the base pressure is assumed constant at the separation value.By combining this potential flow analysis with boundary layer calculations for the attached part of flow, the pressure distribution over airfoil surface, the maximum lift coefficient of multielement airfoil sections and its dependence on REYNOLDS number can be calculated.Comparisons of the present method with experimental data and other methods are presented for several airfoil sections. The predicted curves of aerodynamic coefficients for the NACA 4412 airfoil section and the NACA 23012 with a slat and a slotted flap are compared with experiments.
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