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This paper presents experimental results obtained with passive high lift systems using a combination of smart flap kinematics and vortex generators. A mid-scale 2.5D wind tunnel model based on DLR-F15 is tested in INCAS Subsonic Wind Tunnel, swept at 30 deg, incorporating the slat, 54 flap/VG/chord extension configurations and test matrix, developed by Dassault-Aviation. INCAS designed, manufactured and instrumented components to be added to the existing INCAS-F15 2D wind tunnel model. The test campaign was completed and results are presented.

Following the successful results of the test campaign on 2D configuration of the oscillatoryblowing system in the flap gap of the INCAS F15 wind tunnel model, extensive evaluation of the 2.5Deffects have been initiated in order to enable solid understanding of the fluidic integrationsmechanisms and to validate this technology at a higher TRL level. Initial experiments on 2Dconfiguration were based on work performed in AVERT EU FP6 project where the oscillatory flapgap blowing system was designed and tested on a INCAS F15 2D wing model. In 2.5D test cases thiswork has been extended so that the proposed system may be selected as a mature technology in theJTI Clean Sky, Smart Fixed Wing Aircraft ITD. New experimental setup was used and also updatedelectronics for the blowing system have been introduces. This was complemented by a new extensionfor the data acquisition system and visualization tools. Complex post-processing of the experimentaldata was mainly oriented towards system efficiency and TRL evaluation for this active technology.