22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-2.7.1

THE APPLICATION OF A TIME ACCURATE UNSTRUCTURED EULER SOLVER COUPLED WITH A BOUNDARY LAYER SOLVER FOR THE SOLUTION OF TRANSONIC AEROELASTIC PROBLEMS ON COMPLEX CONFIGURATIONS

S. A.Galpin
BAE SYSTEMS Airbus, UK

Keywords: aeroelastics, complex configurations, euler, time-accurate, unsteady

Transonic aeroelastic experience on Airbus aircraft has shown that purely linear Computational Fluid Dynamics methods, are lacking sufficient accuracy for high Mach numbers (M>0.7) on high aspect ratio configurations. For these configurations, aeroelastic responses can be highly non-linear, due to transonic aerodynamic effects. In order to predict these non-linear aerodynamic pressures and forces, a time-accurate, unstructured Euler solver, coupled with a 2D boundary layer method, has been developed. Steady state unstructured Euler solvers have evolved significantly over recent years, and are now used routinely by the Airbus UK for modelling steady state 3D flows around complex geometry. The ability to model complex wing/body/nacelle/pylon configurations, in a time-accurate environment is seen as a significant increase in capability. It is intended that a time-accurate unstructured Euler solver would be used to complement existing linear CFD methods for aeroelastic design work.

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