Aerodynamic Optimization of a High Speed Civil Transport on Parallel Computers

A design methodology which uses a variable-complexity modeling approach in conjunction with response surface approximation methods has successfully been developed. This approach uses simple models to improve the accuracy of the response surface and reduce the number of analyses based on complex models required for constructing the surface. Simple models are rst used to eliminate \nonsense" portions of the design space. Then a response surface based on the simple models is used to reduce the number of unknown coeecients that deene the response surface. This approach is applied to an example problem of wing design for a High Speed Civil Transport (HSCT) aircraft involving a subset of four HSCT wing design variables.