In Civil Transport Team of Japan Aerospace Exploration Agency, researches to develop design technologies for advanced high-lift devices in the aerodynamics and aeroacoustics have been conducted combining CFD and wind tunnel testing. A series of wind tunnel testing using a realistic civil aircraft high-lift model have been conducted from 2005 to 2008. In this paper, several computational studies related to the wind tunnel tests for high-lift aerodynamics are presented. Influence of the boundary layer transition with a transition prediction method based on eN method and semi-empirical approaches is evaluated. The influence of brackets to support the high-lift devices is also discussed and interference of disturbed wakes by the supports to the flows is shown. CFD investigation of wind tunnel wall interferences using half-span testing model shows the influence of the boundary layer spacer to the flow and the best height of the spacer. Investigations of the interferences between the nacelle-pylon and high-lift devices with nacellechine effect and setting effect of high-lift devices and their CFD predictions are also shown. The capability and research areas required for further efforts are discussed.
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