Numerical Studies of Active Flow Control applied at the Engine-Wing Junction

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Kurzfassung

This paper presents a numerical study of active flow control applied at the engine-wing junction of a generic full scale wind tunnel model representing a landing configuration to increase the high-lift performance. The use of UHBR (Ultra High Bypass Ratio) engines is currently one of the most promising approaches to further increase the efficiency of transport aircraft. However their large engine diameter also compromises the aerodynamic efficiency of airliners with engines mounted under backward swept wings. In order to keep a low ground clearance to avoid a heavy landing gear extension the large UHBR engine nacelles have to be closer coupled to the wing. This prevents the mounting of leading edge high-lift devices at the nacelle-wing junction such as slats, Krueger flaps or droop noses at the junction and leads to a local flow separation on the wing suction side in the wake of the nacelle which may trigger the total wing stall. This reduces the maximum lift coefficient which is a sizing parameter of the high-lift system. In order to reduce the size of the high-lift system and hence increase the overall aircraft efficiency this local flow separation has to be suppressed. Within the European project AfloNext (Active Flow - Loads and Noise control) the use of AFC (Active Flow Control) for the suppression of this flow separation is studied with high-fidelity numerical simulations and experimental studies with a full scale wind tunnel model. At the German Aerospace Center (DLR) numerical studies with steady and pulsed jet blowing are performed to determine working operation parameters of the actuators. In this contribution the first results of this study are presented.

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• Numerical Studies of Active Flow Control applied at the Engine-Wing Junction. (deposited 22 Jan 2015 14:51) [Gegenwärtig angezeigt]