The Calculation of the Lift Distribution and the Near Vortex Wake Behind High and Low Aspect Ratio Wings in Subsonic Flow,

A method is presented for the combined calculation of the lift and lift distribution on a wing and also of the trailing vortex flow behind the wing. It is assumed that the lift of a wing is generated by a system of vortices distributed over the complete wing planform and shed away from each elemental area on the planform. Using the concepts of the vortex lattice method, it is assumed in the linear lift variation case, that the vortices are aligned on the wing planform and are shed away from the trailing edges. Vortex line interaction calculations for the trajectories of the vortex lines are programmed. As a result, the leading edge lift vortices which are obtained on slender wings can now be handled. This report contains a description of the numerical method. (Author Modified Abstract)