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AFloWTest

Wind tunnel test for flow control at the engine/pylon with a representative aircraft configuration under fully realistic flow conditions

Total Cost €

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EC-Contrib. €

0

Partnership

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Project "AFloWTest" data sheet

The following table provides information about the project.

Coordinator
STICHTING NATIONAAL LUCHT- EN RUIMTEVAARTLABORATORIUM 

Organization address
address: Anthony Fokkerweg 2
city: AMSTERDAM
postcode: 1059CM
website: www.nlr.nl

contact info
title: n.a.
name: n.a.
surname: n.a.
function: n.a.
email: n.a.
telephone: n.a.
fax: n.a.

 Coordinator Country Netherlands [NL]
 Total cost 942˙500 €
 EC max contribution 942˙500 € (100%)
 Programme 1. H2020-EU.3.4.5.1. (IADP Large Passenger Aircraft)
 Code Call H2020-CS2-CFP03-2016-01
 Funding Scheme CS2-RIA
 Starting year 2017
 Duration (year-month-day) from 2017-01-01   to  2018-12-31

 Partnership

Take a look of project's partnership.

# participants  country  role  EC contrib. [€] 
1    STICHTING NATIONAAL LUCHT- EN RUIMTEVAARTLABORATORIUM NL (AMSTERDAM) coordinator 870˙000.00
2    TECHNISCHE UNIVERSITEIT DELFT NL (DELFT) participant 72˙500.00

Map

 Project objective

The Active Flow Wind tunnel Test (AFloWTest) project considers the testing of a realistic high lift configuration half-model with a large and with a Ultra High Bypass Ratio (UHBR) flow-through nacelle. An existing half model will be adapted with an UHBR nacelle and for the application of Active Flow Control (AFC) systems at the upper side of the wing near the wing pylon interface in order to improve the high lift performance of the configuration. The application of AFC is considered in order to diminish the detrimental effects of applying a large nacelle in close proximity of the wing, necessitating a slat cutback. Different AFC systems will be installed and tested: a Pulsed Jet Actuator (PJA) and a Steady Blowing (SB) device. Each will be tested at one position. Low speed tests (Ma=0.1 to 0.3) need to be made at representatively high Reynolds number. With the target half model sufficiently high Reynolds number (Re based on mean aerodynamic chord) can only be obtained in a highly pressurized wind tunnel or in a cryogenic facility. The DNW-KKK cryogenic wind tunnel has been selected for the test. Overall model forces will be measured and local influence of the AFC systems needs to be monitored, using surface streamline pattern visualization with mini-tufts, complemented with detailed PIV measurements of the separated flow and flow topology over the wing downstream of the wing pylon/nacelle interface.

 Publications

year authors and title journal last update
List of publications.
2018 Vlad Ciobaca, Bruno Stefes, Anton de Bruin, Matthias Bauer, Philipp Schlösser, Arnoud de Blécourt, Niko Bier, Junnai Zhai, Michael Meyer, Jochen Wild
WIND TUNNEL EXPERIMENTS WITH LOCAL ACTIVEFLOW CONTROL FOR AIRCRAFT TOWARDS FUTUREFLIGHT TESTING
published pages: , ISSN: , DOI:
31th Congress of the International Councel of Aeronautical Sciences (ICAS) September 9-14, 2018 2019-07-18

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The information about "AFLOWTEST" are provided by the European Opendata Portal: CORDIS opendata.

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