Abstract:

This paper introduces and develops a nonlinear theory that extends the linear Prandtl Lifting Line theory. Lifting Line theory works well for wings with large aspect ratios, but fails for wings with small aspect ratios. In the context of Micro Aerial Vehicles (MAVs), the size constraints impose a need for wings and control surfaces with small aspect ratios. Hence, a nonlinear theory is introduced in this paper. The theory uses a system of vortices with variable strength, and using the boundary conditions, solves for vortex strength. Using that, we are able to find the lift generated by the given surface. I extend this by considering control surfaces where the angle of attack is changed and investigate the response of lift. This response is then compared with response of general aircraft airfoils.