ATTESI
Active Flow Control Technique on Trailing Edge Shroud for Improved High Lift Configurations
| Coordinatore | TECHNISCHE UNIVERSITAT BRAUNSCHWEIG
Organization address
address: POCKELSSTRASSE 14 contact info |
| Nazionalità Coordinatore | Germany [DE] |
| Totale costo | 459˙780 € |
| EC contributo | 344˙834 € |
| Programma | FP7-JTI
Specific Programme "Cooperation": Joint Technology Initiatives |
| Code Call | SP1-JTI-CS-2010-04 |
| Funding Scheme | JTI-CS |
| Anno di inizio | 2011 |
| Periodo (anno-mese-giorno) | 2011-06-01 - 2014-02-28 |
Partecipanti
| # | ||||
|---|---|---|---|---|
| 1 |
TECHNISCHE UNIVERSITAT BRAUNSCHWEIG
Organization address
address: POCKELSSTRASSE 14 contact info |
DE (BRAUNSCHWEIG) | coordinator | 145˙991.00 |
| 2 |
TOTALFORSVARETS FORSKNINGSINSTITUT
Organization address
address: Gullfossgatan 6 contact info |
SE (STOCKHOLM) | participant | 99˙375.00 |
| 3 |
IBK-INNOVATION GMBH & CO. KG
Organization address
address: REHDORFER STRASSE 4 contact info |
DE (NUERNBERG) | participant | 85˙700.02 |
| 4 | IBK INGENIEURBUERO HAUPTSITZ | DE | participant | 13˙767.98 |
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Obiettivo del progetto (Objective)
'The subject of the proposed project ATTESI is the design and evaluation of flow control techniques to improve the separation behavior on a drooped spoiler configuration. The proposed project comprehends numerical evaluation and optimization of the spoiler droop together with different flow control approaches applied upstream of the kink (the effect of the droop) and at the trailing edge of the spoiler. The techniques are the application of fluidic vortex generator jets (VGJs) upstream of the kink and a fluidic gurney (FG) at the trailing edge of the spoiler. The two AFC-techniques will be able to operate both in static and in pulsed (dynamic) mode. The pulsed VGJs will be designed in a two-step-procedure using state-of-the-art numerical tools to generate a validation dataset and experience the basic sensitivities. Further design and optimization will be performed based on a statistical model. The fluidic gurney will be applied at the lower side of the trailing edge. It will be designed within a numerical optimization loop together with the spoiler droop angle. The numerical analysis will be accompanied by experimental work that will be conducted in the 1.3m-windtunnel at TU-BS up to Reynolds numbers of 2 Mio. The VGJs as well as the fluidic gurney will be integrated into a drooped spoiler model of an airfoil model with DLR-F15 contour. The proposed project will cover the elaboration of a structural model for the drooped spoiler consisting of a “smart surface”, which enables to droop the spoiler while remaining a smooth surface. The structural design will be based on finite element analysis and will be continued within the project to a demonstrator model for the smart surface. The results will be analyzed with respect to effectiveness, efficiency and towards swept wings.'