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Useful PLASMa for AEROdynamic control

Project information

Grant agreement ID: 234201

Status

Closed project

  • Start date

    1 October 2009

  • End date

    31 December 2012

Funded under:

FP7-TRANSPORT

  • Overall budget:

    € 4 988 029,40

  • EU contribution

    € 3 815 410

Coordinated by:

OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES

France

Objective

PLASMAERO seeks to demonstrate how surface & spark discharge plasma actuators could be used to control aircraft aerodynamic flow. This will be achieved through an enhanced understanding of their physical characteristics and an in-depth study of how they may be optimised to influence the air flow properties. The project will run for 36 months and will show the advantages and notably the ease of implementation that these innovative devices have over other potential active actuators. The project objectives are: Understand, model and classify, through experimental and numerical studies, the most relevant physical characteristics of surface and jet plasma actuators capable of influencing airflow; Perform comparative experimental tests & numerical studies of different actuator configurations to select the most promising for further development; Demonstrate through wind tunnel experimentations the ability of plasma devices to significantly influence the aerodynamics in terms of lift, lift/drag and high lift noise in representative aeronautical airflow conditions (take-off, cruise and landing). Demonstrate the easy-of-use and installation of these actuators in a reduced size flight platform. Provide exhaustive recommendations on future work to be performed to achieve the implementation of this technology base on next generation aircraft programmes. The work will be concentrated on the factors influencing lift and notably through the reduction of separation, of tip vortex and through delayed transition for take-off and landing and influencing lift/drag through controlling the shock/boundary layer interaction induced turbulent separation for cruise conditions. The results of this work will demonstrate to the aircraft industry the advantages of this technology both in terms of ease of use and integration possibilities on the airplane. This proposal for a Level 1 project is submitted by 12 partners in the Call FP7-RTD-2008.

Coordinator

OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES

Address

Chemin De La Huniere
91120 Palaiseau

France

Activity type

Research Organisations

EU Contribution

€ 1 058 384

Administrative Contact

Brigitte Giacomi (Ms.)

Participants (10)

ARTTIC

France

EU Contribution

€ 165 140

C.I.R.A. CENTRO ITALIANO RICERCHE AEROSPAZIALI SCPA

Italy

EU Contribution

€ 299 840

CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE CNRS

France

EU Contribution

€ 805 245

ECOLE POLYTECHNIQUE FEDERALE DE LAUSANNE

Switzerland

EU Contribution

€ 384 177

SAFRAN AIRCRAFT ENGINES

France

EU Contribution

€ 20 875

STICHTING NATIONAAL LUCHT- EN RUIMTEVAARTLABORATORIUM

Netherlands

EU Contribution

€ 150 000

TECHNISCHE UNIVERSITAT DARMSTADT

Germany

EU Contribution

€ 253 500

INSTYTUT MASZYN PRZEPLYWOWYCH IM ROBERTA SZEWALSKIEGO POLSKIEJ AKADEMII NAUK - IMP PAN

Poland

EU Contribution

€ 139 999

THE UNIVERSITY OF NOTTINGHAM

United Kingdom

EU Contribution

€ 248 250

UNIVERSITY OF SOUTHAMPTON

United Kingdom

EU Contribution

€ 290 000

Project information

Grant agreement ID: 234201

Status

Closed project

  • Start date

    1 October 2009

  • End date

    31 December 2012

Funded under:

FP7-TRANSPORT

  • Overall budget:

    € 4 988 029,40

  • EU contribution

    € 3 815 410

Coordinated by:

OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES

France