Flight Test Tailored ETW Testing of a Commercial Transport High Lift Configuration

Abstract

The present contribution describes the set-up and major results of a low speed test with an Airbus A320 wind tunnel model in high lift configuration in the ETW under cryogenic high pressure test conditions. The test is embedded in the joint LuFo IV research project HINVA (High Lift INflight Validation). The overall objective of the HINVA project is to improve the capability of CFD tools and wind tunnel testing to predict maximum lift and its determining flow phenomena in terms of accuracy and reliability. The reference for both simulation approaches is given by dedicated flight test data obtained in a flight test campaign using DLR’s ATRA test aircraft. In particular, the static aero-elastic deformations from the flight test at maximum lift conditions have been incorporated in the wind tunnel model. Moreover, attention is paid to the scaled representation of geometric features, such as slat tracks or a de-icing pipe between slat and fixed wing. The peniche height of the A320 half model is adapted to maximum lift conditions. The model is equipped with a high resolution pressure tap distribution aligned to the pressure measurement locations of the flight test aircraft. In addition to standard force, moment and pressure measurements, cryo PIV velocity field measurements have been carried out above the wing aft of the engine, as well as transitions measurements based on temperature sensitive paint. The deformation under wind loads is detected by a stereo pattern tracking system. After introducing the considerations for the model layout, the test techniques in use are introduced with selected results presented for each technique.