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TFAST

Financiado

Cerrado

Transition Location Effect on Shock Wave Boundary Layer Interaction

Vision-2020, whose objectives include the reduction of emissions and a more effective transport systems, puts severe demands on aircraft velocity and weight. These require an increased load on wings and aero-engine components. The... ver más

31/01/2016

IMP-PAN

5M€

Presupuesto del proyecto: 5M€

Líder del proyecto

INSTYTUT MASZYN PRZEPLYWOWYCH IM ROBERTA SZEW... 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 14 Participantes

Financiación concedida El organismo FP7 notifico la concesión del proyecto el día 2016-01-31 No tenemos la información de la convocatoria

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14 Participantes

IMP-PAN

0.00€ | Lider

TU Delft

N.D. | Participante

INPT

N.D. | Participante

CNRS

N.D. | Participante

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Líder del proyecto

INSTYTUT MASZYN PRZEPLYWOWYCH IM ROBERTA SZEW... 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 Vision-2020, whose objectives include the reduction of emissions and a more effective transport systems, puts severe demands on aircraft velocity and weight. These require an increased load on wings and aero-engine components. The greening of air transport systems means a reduction of drag and losses, which can be obtained by keeping laminar boundary layers on external and internal airplane parts. Increased loads make supersonic flow velocities more prevalent and are inherently connected to the appearance of shock waves, which in turn may interact with a laminar boundary layer. Such an interaction can quickly cause flow separation, which is highly detrimental to aircraft performance, and poses a threat to safety. In order to diminish the shock induced separation, the boundary layer at the point of interaction should be turbulent. The main objective of the TFAST project is to study the effect of transition location on the structure of interaction. The main question is how close the induced transition may be to the shock wave while still maintaining a typical turbulent character of interaction. The main study cases - shock waves on wings/profiles, turbine and compressor blades and supersonic intake flows - will help to answer open questions posed by the aeronautics industry and to tackle more complex applications. In addition to basic flow configurations, transition control methods (stream-wise vortex generators and electro-hydrodynamic actuators) will be investigated for controlling transition location, interaction induced separation and inherent flow unsteadiness. TFAST for the first time will provide a characterization and selection of appropriate flow control methods for transition induction as well as physical models of these devices. Emphasis will be placed on closely coupled experiments and numerical investigations to overcome weaknesses in both approaches.

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