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PLASMAERO

Financiado

Cerrado

Useful PLASMa for AEROdynamic control

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-... ver más

31/12/2012

ONERA

5M€

Presupuesto del proyecto: 5M€

Líder del proyecto

OFFICE NATIONAL DETUDES ET DE RECHERCHES AERO... No se ha especificado una descripción o un objeto social para esta compañía.

TRL 4-5

Fecha límite participación Sin fecha límite de participación.

Ver 11 Participantes

Financiación concedida El organismo FP7 notifico la concesión del proyecto el día 2012-12-31 No tenemos la información de la convocatoria

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Información adicional privada

No hay información privada compartida para este proyecto. Habla con el coordinador.

11 Participantes

ONERA

0.00€ | Lider

THE UNIVERSITY OF NOTTINGHAM

N.D. | Participante

TECHNISCHE UNIVERSITAT DARMS...

N.D. | Participante

CNRS

N.D. | Participante

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Líder del proyecto

OFFICE NATIONAL DETUDES ET DE RECHERCHES AERO... No se ha especificado una descripción o un objeto social para esta compañía.

TRL 4-5

Presupuesto del proyecto 5M€

Fecha límite de participación Sin fecha límite de participación.

Descripción del proyecto 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.

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