Extended Nonlinear Lifting-Line Method for Aerodynamic Modeling of Reconfigurable Aircraft

Cl = section lift coefficient c = local chord length D = fading-memory constant G = nondimensional circulation l = section lift force/length m = number of points used in sine series expansion of circulation function N = consecutive iterations convergence parameter r = perpendicular distance from vortex tol = iteration relative tolerance of conversion U1 = freestream velocity magnitude w = downwash velocity y0 = wing semispan, y coordinate of wingtip = wind incidence angle, wing angle of attack eff = effective angle of attack 2D = 2-D vortex-induced wind incidence angle 3D = 3-D wake-induced wind incidence angle = circulation magnitude = nondimensional spanwise coordinate = local wing twist angle = local wing sweep angle = nondimensional chordwise coordinate = air density = trigonometric spanwise coordinate