Reduction of induced drag in conguration flight using wing twist at post-stall angles of attack

In this paper, a novel decambering technique has been implemented using a vortexlattice method to study the effects of wing twist on the induced drag of individual lifting surfaces in congurationight. The effects of both geometric and aerodynamic twist arestudied. 2D Cl−α and Cm−α from XFoil at Re = 1×106for NACA0012 airfoil is used as inputto predict 3D post-stall aerodynamic characteristics for a single wing with geometric twistand compared with literature. Aerodynamic twist is implemented by using dierent airfoilsalong wing-span and wing CL−α and Cdi−α aare compared with experiment. The effect ofasymmetric aerodynamic twist on the leading wing shows distinct changes in the span-wisedistribution of Cland Cdion the trailing wing and throws up interesting inferences aboutformation ight aerodynamics.