First measurements on an Airbus high lift configuration at ETW up to flight Reynolds number

The capability of the European Transonic Windtunnel ETW to test simultaneously at cryogenic temperatures down to 110 K and at pressure levels ranging from 100 kPa up to 450 kPa allows to perform separated experimental investigations of pure Reynolds number and aeroelastic effects. This capability combined with the recently established half model test system has been used to carry out the first test campaign with a high lift configuration in the low Mach number range. Experimental investigations and analytical work was performed as task of the European research project EUROLIFT which forms part of a “European High Lift Programme”. The present paper provides information about the background of the test campaign and specific model features. Typical findings on the ”clean wing” as well as for a “landing” configuration are described with special emphasis on Reynolds number effects. The benefit of a capability to operate from minimum up to flight Reynolds number is documented with reference to scaling effects. To validate ETW for testing high lift configurations at low speeds, gained results have been referenced to data recorded in the Airbus LSWT facility and the German - Dutch windtunnel KKK. Also flight data could be made available for quality comparison.