Abstract

The objective of this paper was to model the stability and control derivatives using Computational Fluid Dynamics (CFD). This would provide a more reliable tool in the development of aircraft. This process could reduce the reliance on wind tunnel results with a consequent reduction in development costs. The test model used for this paper was a specialised delta wing configuration. The study was undertaken by comparing simulation parameters and determining their effects on the flow characteristics. The simulation was undertaken using internal meshing software, the flow simulation software TAU and the graphical interface Tecplot. Results showed that a single CFD model could not be used for the prediction of aerodynamic behaviour under the full range of angle of attack (0° to 25°). However the surface mesh refinement and optimisation of simulation parameters allowed for a better prediction at lower angle of attack (0° to 15°). The dynamic simulation showed that flow characteristics were better captured for higher pitching frequencies. Overall the study will assist the progress of future studies.

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