Computation of non-linear dynamic derivatives around a specialised delta wing configeration

The goal of this paper was to determine the feasibility to accurately model stability and control derivatives using Computational Fluid Dynamics (CFD) applications. If successful, this would be the first step towards CFD being utilised as a more reliable tool in the development of aircraft. The test bed used for this paper was based on a specialised delta wing configuration. The analysis was completed using specialised meshing software, the flow simulation software (TAU) developed by the German Aerospace Agency (DLR) and the graphical interface Tecplot. The focus of the work was on the computation of the pitch oscillation in the interesting angle of attack range. The results found were promising though they still indicated that further research in this field is required to ensure true dependability on CFD results. The recommendations found would help to ensure the progress of future findings.