Simulation of stall, spin, and recovery of a general aviation aircraft

A nonlinear lifting line-vortex lattice aerodynamic model has been developed for use with a computer 6-DOF vehicle motion simulation for the purpose of studying the behavior of general aviation-type aircraft at high angles of attack. The model includes the unsteady wake effects due to a discrete, nonplanar vortex system. Each lifting surface is modeled with discrete vortex segments and their associated control points. Selected lifting surface segments can have their lift-curve properties changed to simulate control deflections. This model is used to simulate the stall entry, departure, subsequent spin, and recovery of a general aviation aircraft. (Author)