| Abstract: | Contributions to the aerodynamics development have to be involved to achieve an increase in quality, reducing time and computer costs. Therefore, this work develops an optimization method based on the finite volume explicit Runge–Kutta multi‐stage scheme with central spatial discretization in combination with multigrid and preconditioning. The multigrid approach includes local time‐stepping and residual smoothing. Such a method allows getting the goal of compressible and almost incompressible solution of fluid flows, having a rate of convergence almost independent from the Mach number. Numerical tests are carried out for the NACA 0012 and 0009 airfoils and three‐dimensional wings based on NACA profiles for Mach‐numbers ranging from 0.8 to 0.002 using the Euler equations. These calculations are found to compare favorably with experimental and numerical data available in the literature. Besides, it is worth pointing out that these results build on earlier ones when finding appropriate new three‐dimensional aerodynamical geometries. Copyright © 2004 John Wiley & Sons, Ltd. |
