Wing's optimization design using serial and parallel computations based on N-S equations

The serial and parallel flow field solution program was validated at two Mach numbers between 0.7 and 0.9 using both a high and a moderate aspect ratio wings. The result based on the Navier-Stokes (N-S) equations proved it right and the parallel efficiency as well as speed-up ratio was discussed. With the goal of maximizing lift-to-drag ratio, the optimization of three-dimensional wing's section thickness and twist angle was discussed. N-S equations as flow field solver and Powell method were used as design tools, and the wing's aspect shape was fixed. The subcritical parallel computation case and supercritical serial computation case demonstrated that nonlinear distribution of thickness and negative twist angle could ameliorate the condition of flow field around the wing, which lead to a higher lift-to-drag ratio. The optimization method is effective.