| An algorithm for the design of two-dimensional aerodynamic shapes was developed, tested, and evaluated. By using combinations of polynomial expressions for the camber line and thickness distributions of an airfoil section, the geometry of an airfoil section may be expressed in terms of a few parameters. The parameters for the airfoil section most closely corresponding to a user-specified airfoil pressure distribution were found through the use of numerical optimization techniques and a simple vortex panel algorithm as a flow field analysis tool.; The design algorithm was evaluated by deriving the sections of well-known airfoils from their calculated pressure distributions. The algorithm has shown itself to have some success in the design of airfoil sections; however, more general descriptions of airfoil camber line and thickness distributions may need to be incorporated into the design algorithm. Also, additional efforts to minimize the number of flow field solutions need to be made. |
