Low-Order Method for Prediction of Separation and Stall on Unswept Wings

A low-order method is presented for aerodynamic prediction of wings operating at near-stall and post-stall flight conditions. The intended use in design, modeling, simulation. In this method, the flow separation due to stall modeled a vortex lattice framework as an effective reduction camber, or “decambering.” For each section wing, parabolic decambering flap, hinged location section, calculated through iteration ensure that lift moment coefficients match with values from two-dimensional viscous input curves angle attack section. As improvement earlier methods, also predicts pattern on wing. Results unswept having various airfoils, aspect ratios, taper small, quasi-steady roll rates, are shown agree well experimental results literature, computational solutions obtained part current work.