Incorporating Nonlinear Aerodynamic Methods Into Transonic Preliminary Design Of A Wing

Abstract

Nonlinear, high delity aerodynamic analysis methods are considered computationally expensive and impractical for use in the preliminary design investigations. In lieu of nonlinear aerodynamic analysis methods, linear aerodynamic analysis tools are often utilized in the execution of preliminary design tasks. Within the preliminary design environment, linear aerodynamic analysis codes are considered accurate in low Mach number ight regimes, but are not considered accurate when analyzing nonlinear ow phenomena. This work demonstrates that nonlinear aerodynamic methods are necessary when developing the preliminary design of a vehicle that operates in the transonic ight regime. An empirical study was carried out where linear and nonlinear aerodynamic methods were utilized independently to optimize a wing that was subjected to stress and rolling moment constraints. Initially, only structural sizing parameters were considered in the design space, but the design space was later expanded to include aerodynamic shape variables. The design investigations executed in this investigation were carried out at Mach numbers 0.50 and 0.89. At Mach 0.50, the linear and nonlin-