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Model Testing of High Lift system

The High Lift devices development for small aircrafts has started in a first Clean Sky 2 research phase by selecting several innovative high-lift devices for two different types of SAT aircraft architectures. At the end of the op... ver más

31/08/2021

VON KARMAN INSTITU...

799K€

Presupuesto del proyecto: 799K€

Líder del proyecto

VON KARMAN INSTITUTE FOR FLUID DYNAMICS No se ha especificado una descripción o un objeto social para esta compañía.

TRL 4-5

Fecha límite participación Sin fecha límite de participación.

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Financiación concedida El organismo H2020 notifico la concesión del proyecto el día 2021-08-31

JTI-CS2-2018-CFP09-AIR-02-71: Model Manufacturing and Wind Tunnel...

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Cerrada hace 6 años

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

2 Participantes

VON KARMAN INSTITUTE FOR FLU...

343.75K€ | Lider

SONACA SA

455.51K€ | Participante

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Duración del proyecto: 23 meses Fecha Inicio: 2019-09-19
Fecha Fin: 2021-08-31

Líder del proyecto

VON KARMAN INSTITUTE FOR FLUID DYNAMICS No se ha especificado una descripción o un objeto social para esta compañía.

TRL 4-5

Presupuesto del proyecto 799K€

Fecha límite de participación Sin fecha límite de participación.

Descripción del proyecto The High Lift devices development for small aircrafts has started in a first Clean Sky 2 research phase by selecting several innovative high-lift devices for two different types of SAT aircraft architectures. At the end of the optimization of the aerodynamic and integration design, the different high-lift devices will be classified based upon the benefits of the high lift architectures, and the most suitable design will be selected. From this input, the current proposal will perform Wind Tunnel validation testing of a selected SAT Aircraft High Lift devices System. This validation objective includes the construction of an instrumented model with a segment of wing box including the leading/trailing edge high lift devices, and their aerodynamic characterization by performing tests in a large wind tunnel. An experimental assessment will provide a comparison of the performance and recommendations on the tested High Lift solutions. The research will implement a specific wind tunnel model, designed and manufactured to provide variable positions of flap with respect to the main wing body. Different angles of attack will be tested. Manufactured with the required aerodynamic quality, the model will be installed in the large VKI subsonic wind tunnel and tested at the required Reynolds number. A concept of flap separation control jet blowing system installed at the main wing box trailing edge will also be tested. The tests will be performed with the support specifically designed and manufactured high lift devices models positioning brackets, existing turn table and load balance equipment, and specific interface plates and side walls. Wind tunnel measurements (pressure, force) will be implemented and these measurements will be complemented with PIV measurements for flow field visualization and detailed flow characterization (mean and unsteady behavior). Finally, the performance of the leading & trailing edge high lift solution will be analyzed.

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