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.
The amount of lift produced by an aircraft wing is important in the aerospace industry. High-lift systems, which include wing flaps and slats, are under development for small aircrafts in a first Clean Sky 2 research phase. After optimising the aerodynamic and integration design, these devices will be classified based on their high lift architectures to shortlist the best design. The EU-funded MOTHIF project will use a specifically designed and manufactured wind tunnel model for testing variable positions of flap and for different angles of attack. Along with the flap separation control jet blowing system installed at the main wing box trailing edge, this will be installed in the VKI subsonic wind tunnel
and tested at the required Reynolds number.
The current project MOTHIF (MOdel Testing of HIgh LiFt system) 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
The project started on 1st of January 2020 for one and a half year under the coordination of the von Karman Institute with a Belgian partner, SONACA S.A. The overall budget of the project is of € 799 260. VKI will make the aerodynamic characterization by performing test in the large low speed wind tunnel. SONACA is in charge of the construction of the instrumented model with a segment of wing box including the trailing edge high lift devices, while Piaggio Aerospace acts a topic manager of the project.
The kick-off meeting was organized at VKI on January 21 and continued at SONACA on Januay 22.
This project has received funding from the Cleansky 2 Joint Undertaking (JU) under grant agreement No 865267.
