Aerodynamic Optimization Using Sensitivity Derivatives from a Three-Dimensional Supersonic Euler Code

Abstract

Initial results from a three-dimensional marching Euler code equipped with an efficient sensitivity analysis capability are presented. The aerodynamic sensitivity derivatives with respect to wing geometry parameters obtained by the incremental iterative method are compared with those obtained by an efficient central finite differencing method and are both accurate and computationally cheaper. Sample cases for a Mach 2.4 high-speed civil transport wing-body configuration are shown that indicate the feasibility of using these sensitivity derivatives in aerodynamic optimization studies. These demonstrations have been given for design variables that determine wing planform and control flap deflections. The filleted wing-body geometry and computational fluid dynamics grid are modified by automated surface geometry and grid generation codes through which sensitivity information is propagated