Influence of Wing Elasticity on the Experimental and Numerical Determination of Dynamic Derivatives

Abstract

The presented investigations deal with the analysis of dynamic derivatives of a modern transport aircraft configuration (DLR-F12). The conducted wind tunnel tests focused mainly on the measurements of unsteady forces, moments and pressure distributions. The measurements of the steady and unsteady wing deformations using two different wings were of significant importance. Those wings are designed to be ideal stiff on the one hand but also to allow more flexibility on the other hand, in order to investigate the effect of wing elasticity on the static and dynamic aerodynamic properties of this configuration. For the validation of the numerical tools calculations are performed based on the solution of the unsteady Reynolds-averaged Navier-Stokes (URANS) equations using a finite volume parallel solution algorithm with an unstructured discretization concept (DLR TAU-Code). The wing deformation is accounted for using the finite element code ANSYS.