Numerical determination of dynamic derivatives for transport aircraft

The represented investigations are concerned with simulations of unsteady aircraft aerodynamics and thus belongs to the research field of computational fluid dynamics (CFD) for aerospace applications. The calculations are based 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). The analysis consists of two parts, in order to obtain a more detailed understanding of the unsteady aerodynamical and flight mechanical behaviour of an airplane. For this purpose systematic investigations have been performed with basic configurations which have NACA0012 profiles (e.g. wing, wing + horizontal tail, wing + vertical tail). The second part of the investigation is the calculation of the dynamic derivatives of a modern transport aircraft configuration (DLR-F12). The objective of this investigation is to adapt the numerical methods for the calculation of dynamic derivatives and to validate the numerical results against windtunnel data