Induced Drag Calculations with the Unsteady Vortex Lattice Method for Cambered Wings

A = panel area, m b = semichord, m c = chord, m Cd = sectional drag coefficient Cl = sectional lift coefficient D = panel drag, N F = force vector, N h = plunge displacement, m k = reduced frequency L = panel lift, N l = vortex segment vector M = number of chordwise panels N = number of spanwise panels n = panel normal vector P = orthogonal projection operator s = nondimensional time U = velocity vector, m · s−1 t = time, s α = angle of attack, rad ∆b = panel span, m ∆c = panel chord, m ∆p = pressure drop Γ = circulation, m · s ω = angular velocity, rad · s−1 *PhD Student, Aerospace and Mechanical Engineering Department, t.lambert@ulg.ac.be †Associate Professor, Aerospace and Mechanical Engineering Department, AIAA Senior Member, gdimitiradis@ulg.ac.be