Abstract
A computing method for calculation of the subsonic, viscous flow around clean wings of moderate to high aspect ratio and low swep has been extended to analyse wings with deployed high-lift systems, that is,wings with deflected leading and/or trailing edge flaps. The overall method.is an iterative procedure combining a 3-d inviscid lifting surface theorywith a 2-d multi-element airfoil analysis procedure including boundary layer effects and a model for rear separation. Also, the ground effects are included by means of reflected image technique and the final solution is improved using a curved basic flow analysis. In this report the total method is briefly described giving the - salient features of the procedure. The results of numerical studies regarding the convergence of the iterations, and validation of the current method against experi mental results are included along with a discussion about present limitations and possible future work
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