Numerical Simulation of Manoeuvring Aircraft by Aerodynamic and Flight-Mechanic Coupling

This paper presents results of simulations performed within the scope of the DLR-Project AeroSUM-Aerodynamic Simulation of Unsteady Manoeuvres. The objective of the AeroSUM-Project is to develop a numerical tool to simulate the unsteady aerodynamics of a free flying aircraft, by use of coupled aerodynamic and flight-mechanic computations. To achieve this objective, the unstructured, time accurate CFD flow-solver Tau is coupled with a computational module solving the flight-mechanic equations of motion. By use of an overlapping grid technique chimera, simulations of a complex configuration with movable control-surfaces is possible. Results of static calculations are presented to show the basic aerodynamics of the vortex dominated flow-field of the delta wing. The static simulation cases also serve as starting solutions for the unsteady simulations. Results of the unsteady manoeuvre simulations are divided into guided motion and free-flight motion. For the guided motion an oscillating motion with a given frequency and amplitude is presented. For the free-flight motion, the following cases are presented free-to-roll from a non-zero initial roll-angle without flap deflection, and free-to-roll initiated by flap deflection from an initial roll-angle of zero. These calculations demonstrate the functionality of the simulation system. A 65-degree cropped delta wing model, with fuselage and movable trailing edge flaps, is used to gather experimental data. Several forced and free-to-roll experiments around the body fixed axes, both with and without flap deflection, are performed in order to validate the computational results obtained with the simulation tool.