BLAME

Breakthrough Laminar Aircraft Model wind tunnel testing in Europe

 Coordinatore STICHTING DUITS-NEDERLANDSE WINDTUNNELS 

 Organization address address: VOORSTERWEG 31
city: Marknesse
postcode: 8316 PR

contact info
Titolo: Mr.
Nome: Oliver
Cognome: Fries
Email: send email
Telefono: +31 527 24 8561
Fax: +31 527 24 8582

 Nazionalità Coordinatore Netherlands [NL]
 Totale costo 988˙756 €
 EC contributo 741˙567 €
 Programma FP7-JTI
Specific Programme "Cooperation": Joint Technology Initiatives
 Code Call SP1-JTI-CS-2013-02
 Funding Scheme JTI-CS
 Anno di inizio 2013
 Periodo (anno-mese-giorno) 2013-12-16   -   2014-06-15

 Partecipanti

# participant  country  role  EC contrib. [€] 
1    STICHTING DUITS-NEDERLANDSE WINDTUNNELS

 Organization address address: VOORSTERWEG 31
city: Marknesse
postcode: 8316 PR

contact info
Titolo: Mr.
Nome: Oliver
Cognome: Fries
Email: send email
Telefono: +31 527 24 8561
Fax: +31 527 24 8582

NL (Marknesse) coordinator 741˙567.00

Mappa


 Word cloud

Esplora la "nuvola delle parole (Word Cloud) per avere un'idea di massima del progetto.

flow    effect    fitted    wing    wind    tunnel    laminar    quality    excellent       flight    dnw    speed    data    wings    model    airbus    blade    ground   

 Obiettivo del progetto (Objective)

'Natural laminar flow wings will be flight tested, within a project called BLADE. A new outer laminar wing will be fitted on the legacy A340-300 wing. A large scale, low speed wind tunnel test in the DNW-LLF (Large Low speed Facility) is offered aiming at generating high quality data allowing flight clearance for the BLADE Flight Test Demonstrator providing know how for performing representative test for future laminar wings. Wind tunnel results will complement results from CFD, especially in ground effect and stall conditions Furthermore testing will allow assessment of basic longitudinal & lateral handling qualities characteristics of the large scale wind tunnel model. The DNW test environment for the wind tunnel model supplied by Airbus features: • A test section size (8 m width and 6 m height), perfectly fitted to the subject wind tunnel model to limit model buoyancy and wall effects • Dorsal sting set-up • Wind speed range (0 – 100 m/s, corresponding to appr. 0.3 Mach number and a Reynolds number of upto 3*106) • Excellent flow quality (very low turbulence level, below 0.1%, which is critical for laminar flow testing) • Innovative ground effect simulation (by means of a moving belt system, capable of running at 80 m/s) • High end data acquisition systems capable of acquiring (un)steady sensor data from model load balances (forces), pressure tabs, Kulites etc. • Flexible data processing systems to convert the acquired data conform Airbus TARDIS (Transnational Aerodynamic Results Data Information System) specification for further analysis purposes. • And last but not least excellent staff, with 35 years of experience in industrial wind tunnel testing as part of aircraft development programs.'

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