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Transition Location Effect on Shock Wave Boundary Layer Interaction

Transition Location Effect on Shock Wave Boundary Layer Interaction

Objective

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.

Coordinator

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

Address

Ul. Fiszera 14
80-231 Gdansk

Poland

Activity type

Higher or Secondary Education Establishments

EU Contribution

€ 258 428

Administrative Contact

Jacek Kordus (Mr.)

Participants (15)

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ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

Germany

EU Contribution

€ 97 000

DASSAULT AVIATION

France

EU Contribution

€ 118 200

CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE CNRS

France

EU Contribution

€ 157 775

OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES

France

EU Contribution

€ 422 750

DLR

Germany

EU Contribution

€ 703 900

NUMERICAL MECHANICS APPLICATIONS INTERNATIONAL SA

Belgium

EU Contribution

€ 303 825

SIEC BADAWCZA LUKASIEWICZ-INSTYTUTLOTNICTWA

Poland

EU Contribution

€ 205 850

SA KHRISTIANOVICH INSTITUTE OF THEORETICAL AND APPLIED MECHANICS OF SIBERIAN BRANCH OF RUSSIAN ACADEMY OFSCIENCE*ITAM OF SB RAS

Russia

EU Contribution

€ 232 900

THE CHANCELLOR MASTERS AND SCHOLARS OF THE UNIVERSITY OF CAMBRIDGE

United Kingdom

EU Contribution

€ 152 800

TECHNISCHE UNIVERSITEIT DELFT

Netherlands

EU Contribution

€ 204 300

UNIVERSITY OF SOUTHAMPTON

United Kingdom

EU Contribution

€ 148 900

UNIVERSITA DEGLI STUDI DI ROMA LA SAPIENZA

Italy

EU Contribution

€ 232 500

THE UNIVERSITY OF LIVERPOOL

United Kingdom

EU Contribution

€ 124 187

INSTITUT NATIONAL POLYTECHNIQUE DE TOULOUSE

France

EU Contribution

€ 161 300

THE PODGORNY INSTITUTE FOR MECHANICAL ENGINEERING PROBLEMS OF NATIONAL ACADEMY OF SCIENCE OF UKRAINE

Ukraine

EU Contribution

€ 43 175

Project information

Grant agreement ID: 265455

Status

Closed project

  • Start date

    1 February 2012

  • End date

    31 January 2016

Funded under:

FP7-TRANSPORT

  • Overall budget:

    € 5 096 031,82

  • EU contribution

    € 3 567 790

Coordinated by:

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

Poland