22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-3.7.3

GROUND EFECT TESTING CAPABILITIES IN THE FILTON 12' X 10' LOW SPEED WIND TUNNEL

M. C. W. Evans
Airbus UK, UK

Keywords: ground effect, filton low -speed wind tunnel

The wind tunnel testing required to simulate the parts of the flight regime close to the ground provides unique challenges. Aerodynamic data is required for these conditions to calculate take off and landing performance to satisfy field length requirements. Traditionally, wind tunnels are used to provide this information. This paper discusses the approach taken by the Filton Low Speed Wind Tunnel in obtaining this data. The technique for testing aircraft models in ground effect in the Filton Low Speed Wind Tunnel is based upon a movable ground plane, which spans the Tunnel Working Section. An innovative system for effectively removing the unrepresentative boundary layer formed on the ground plane has been developed. This is an important part of this technique, which was shown to give results comparable with facilities equipped with a rolling road. The ground plane boundary layer is removed and the flow re-energised by a compressed air driven ejector arrangement. The velocity of the re-energising jet can be controlled to give an integrated boundary layer thickness of zero at the required streamwise position. Results are presented which show general agreement with data from other established ground effect data sources.

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