This proposal deals with an innovative approach to the aerodynamic design of subsonic aircraft, permitting more rapid evaluation of configurations at the early stages of the design process, and enabling preliminary design refinement and optimization. The proposed work involves the development of a practical computational method for aerodynamic design, based on the offerer's widely-used interactive design software. The new method permits rapid computation of three-dimensional lifting surface aerodynamics, avoiding anomalous results that often arise from panel spacing sensitivity in conventional programs. The approach is based on the interpolation schemes developed for vortex-in-cell methods, but retains the computational efficiency of linear methods. In Phase I of this SBIR effort, a pilot code demonstrating the feasibility, efficiency, and robustness of the new method will be developed. If successful, the methodology may form the basis for a new commercial software product and/or may be incorporated into codes currently used by NASA or industry. The approach is especially relevant to general aviation design: its robust, rapid turn-around character makes it well-suited for use by individuals with limited computer resources, or for configuration optimization of interfering systems such as 3-surface designs, canards, or winglets.If the approach is successful it would lead to a commercial software product to be developed by the offeror in Phase II. The technology could be incorporated into numerous, existing commercial and government codes. Such programs would aid general aviation manufacturers in initial design and development of either conventional or innovative configurations.Aerodynamics Optimization Design
