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Investigating active vortex generators as a novel high lift device
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
2006 (English)In: ICAS-Secretariat - 25th Congress of the International Council of the Aeronautical Sciences 2006, Curran Associates, Inc., 2006, Vol. 3, 1472-1483 p.Conference paper, Published paper (Refereed)
Abstract [en]

Within the framework of the HELIX programme [1], a study using experimental and numerical tools was employed to simulate the aerodynamic behavior of a transport aircraft wing profile when equipped with deployable Active Vortex Generators (AVGs). The geometry of the investigated concept consists of a single row array of delta wings positioned above the main airfoil, close to the leading edge, see figure 1. The operational hypothesis of this concept is that the vortex pair generated by the shear layer roll-up at the leading edge of the delta wing will translate downwards. Previous wind tunnel results, obtained for a different wing profile, were promising [5], indicating a possible gain in maximum lift coefficient CLmax of about 0.3 with only small increment in drag and beneficiary stall characteristics. The numerical simulations performed were divided into three different cases: cruise, takeoff and landing configurations. The numerical simulation set-up was a 2.5 dimensional workspace, extruding the profile to a width of one vortex generator. An experimental validation was performed at VZLU:s three meter open low speed tunnel facility. The wind tunnel measurements were performed at a Reynold's number of 1.65.106: The results of the investigation showed that the baseline profile, without the AVGs mounted, produced a higher CLmax and a lower drag than the concept investigated. Possibly, the stall behavior of the AVG concept could be said to have better characteristics than the baseline. The conclusion is that the AVG cannot replace the slat on a late generation wing profile.

Place, publisher, year, edition, pages
Curran Associates, Inc., 2006. Vol. 3, 1472-1483 p.
Keyword [en]
Flow control, High-lift, Vortex generators
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-164225Scopus ID: 2-s2.0-84896971977OAI: oai:DiVA.org:kth-164225DiVA: diva2:805324
Conference
25th Congress of the International Council of the Aeronautical Sciences 2006, 3 September 2006 through 8 September 2006, Hamburg, Germany
Note

QC 20150415

Available from: 2015-04-15 Created: 2015-04-14 Last updated: 2015-04-15Bibliographically approved

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