In this study, Onera M6 wing has been optimized by two parameters, the wing section and the taper ratio, by combining the recent mostly preferable popular approaches, i.e. parallel computing and evolutionary techniques. For the 3-D models, developed during the optimization stages, the mesh required has been generated by using dynamic mesh technique. The code developed for this is robust and faster than the codes that produce mesh only by classical techniques. An Euler flow solver (ACER3D) is used to obtain the flow parameters for each member. From the results, it is observed that the optimization process is working as expected. During the optimization process, the lift coefficient and the thickness ratio are tried to be maintained close to the design values determined at the beginning. The taper ratio becomes smaller and converges to a certain value, while the code tries to minimize the drag force. Additionally, this study can be used as a reference for 2-D or 3-D aerodynamic body optimization by using heuristic-type algorithms, since all details are outlined, referenced, and interpreted with their advantages and disadvantages. Copyright (c) 2007 John Wiley & Sons, Ltd.