Numerical research of dynamic derivatives of unsteady moved aircraft

Abstract

The investigations presented in this lecture notes are concerned with simulation of unsteady aircraft aerodynamics and thus belong to the research field of computational fluid dynamics (CFD) for aerospace applications. For the determination of static and dynamic derivatives the calculations are based on the panel method VSAERO and on the solution of the Reynolds-averaged Navier-Stokes (RANS) equations using the finite volume parallel solution algorithm with an unstructured discretization concept (DLR TAU-code). Systematic investigations have been performed with simple configurations based on NACA0012 airfoil sections (e.g. wing, wing with horizontal tail, wing with vertical tail) in order to obtain a more detailed understanding of the unsteady aerodynamical and flight mechanical behavior of such configurations. Further calculations were performed for a set of experimental data measured on a generic modern transport aircraft configuration (DLR-F12) tested in the 3m Low Speed Wind Tunnel NWB of the German-Dutch Wind Tunnels DNW, Germany, using a unique six degree-of-freedom test rig called 'Model Positioning Mechanism' (MPM). One objective of this investigation is to adapt the numerical methods for the calculations of dynamic derivatives and to validate the numerical methods by means of wind tunnel data.