Abstract
This article describes the development of a semiempirical three-dimensional method for the prediction of maximum lift for complex multielement wing geometries. The method is a combination of cost effective and reliable CFD technology (a surface panel method), and an empirically observed phenomenon occurring at maximum lift conditions that is introduced here as the pressure difference rule. The panel method solutions used in conjunction with the pressure difference rule yield surprisingly accurate predictions of maximum lift for both clean wings as well as multielement wings. Comparisons with experimental data are presented for increasingly complex high-lift wing geometries including full transport aircraft configured for landing.
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