Wing is an important component of airborne glide vehicle which provide the major portion of lift force to be generated and at the same time lift is to be produced with minimum drag. In this paper an optimum design is evolved to provide a high aerodynamically efficient wing in high subsonic regime and at the same time it is subjected to constraints like, it should provide the minimum lift (lateral acceleration as per the guidance demand) to perform flight manoeuvres. The main objective of the work is to maximize the Lift-to-Drag ratio of the wing at a design point subjected to minimum lift requirement. This aerodynamic efficiency (L/D) decides the range performance of a glide vehicle. Wing parameters like span, chord at root, taper ratio and sweep back angle are subjected to optimizer with limits to obtain the best design while the airfoil NACA651 - 412 is same for all the cases. This paper presents the study carried out using design of experiments, surrogate model, evolutionary optimization approach and gradient based optimization approach using MATLABTMsolver. © 2018