Recent applications of advanced computational methods in the aerodynamic design of transport aircraft configurations

Abstract

Aerodynamic designers of transport aircraft have been dreaming for decades of being able to use, for high speed design problems, some of the advanced computational tools that they now have available to them such as the three-dimensional transonic flow methods and three-dimensional finite-difference boundary-layer methods. It is anticipated by the designer and his management that the appropriate use of these new advanced computational methods on the wing design of the next subsonic transport aircraft configuration will typically result in an improved aerodynamic technology level, an improved aerodynamic efficiency for a given level of aerodynamic technology, and reduced design costs through a reduction in the amount of wind tunnel testing required and the resulting shortened time period required to define the final lines.