Modelling High Angle of Attack Aerodynamics of Lambda Wing Planforms

摘要

An extension to the source doublet panel method was implemented in order to model the aerodynamicperformance of delta wing planforms and their derivatives, in this case specically moderately swept lambdawings, where the ow is inuenced by a leading edge vortex system. The method introduces a doubletsheet representing a free shear layer shed from the leading-edge which rolls up over the wing surface. Thesystem of panels including the leading-edge doublet sheet, wing surface and wake is solved using the standardsource-doublet methodology and an iterative scheme is introduced in order to position the leading edge vortexpanels. The lift and pitching moment coeffcients were well predicted when compared with experiments,however there were diu000berences in the size of the leading-edge vortex system. The method is useful in theearly stages of aircraft design in order to conduct parametric studies to assess the changes in lift and pitchingmoment due to changes in planform or sectional geometry.