An Iterative Non-Linear Lifting Line Model For Wings with Unsymmetrical Stall

A numerical non-linear lifting line model is presented which predicts the behavior of a wing beyond the stall given two-dimensional airfoil data. The model, although relatively simple, appears to predict fairly complex stall effects including hysteresis and unsymmetrical spanwise lift distributions with partial-span stall. The numerical model runs rapidly on an IBM-Compatible PC and does not require any extensive CFD-type of calculations. Because of its speed and apparent accuracy in modeling the physical behavior of a stalled wing, it may find application to the simulation of airplane motion beyond the stall. Although the numerical model was developed independently here a similar approach has been tried previously by others. These previous efforts and a comparison with the present results are discussed briefly.