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TRIMIS

COMbined Passive and Active Flow Control Technology Wing

PROJECTS
Funding
European
European Union
Duration
-
Status
Complete
Geo-spatial type
Other
Total project cost
€2 091 693
EU Contribution
€1 744 927
Project Acronym
COMPACT
STRIA Roadmaps
Vehicle design and manufacturing (VDM)
Infrastructure (INF)
Transport mode
Airborne icon
Transport policies
Other specified
Transport sectors
Passenger transport,
Freight transport

Overview

Call for proposal
H2020-CS2-CFP08-2018-01
Link to CORDIS
Objectives

The aim of this project is to design and manufacture a large Hybrid Laminar Flow Control (HLFC) half model, representative of a civil transport aircraft wing, for installation in the ONERA S1MA tunnel. The model will be capable of testing the effectiveness of laminar flow control devices at transonic speeds (M~0.85) and high Reynolds number (>10x10x6/m).

The model will incorporate systems for delaying transition in the leading-edge region over 2 spanwise sections. The outer section will address the HLFC requirements, using either active suction through the surface of the porous wing leading edge and or passive control. The active suction control methods will consist of a porous skin and the wing will incorporate pipework permitting suction to be applied through the porous surface using a suction source provided by the wind tunnel. The location of boundary layer transition at each section will be measured using the IR technique and the upper wing surface will therefore include an insulating material for the measurement of transition using IR thermography. As with all HLFC models, the surface finish will be very high quality with no steps or gaps. The suction system and instrumentation will be fully tested prior to delivery of the model. The inboard part of the wing will be equipped with both passive and active (wall suction) anti-contamination devices to investigate ways to control attachment line transition.

The model will be fitted with a range of instrumentation including pressure tapping's, unsteady pressure transducers, accelerometers, strain gauges and possibly hot films, all of which will be thoroughly tested during final assembly. Finally, on completion of the model assembly, the model deformation due to representative applied static loads will be measured.

Funding

Parent Programmes
Institution Type
Public institution
Institution Name
European Commission
Type of funding
Public (EU)
Specific funding programme
H2020-EU.3.4.5.1.
Other Programme
JTI-CS2-2018-CfP08-LPA-01-51 Design and manufacturing of a large-scale HLFC wing model for a transonic WTT

Partners

Lead Organisation
Organisation
Aircraft Research Association Limited
Address
Manton Lane, Bedford, MK41 7PF, United Kingdom
Organisation website
EU Contribution
€935 809
Partner Organisations
Organisation
Ibk-Innovation Gmbh & Co. Kg
Address
BUTENDEICHSWEG 2, 21129 HAMBURG, Germany
Organisation website
EU Contribution
€374 500
Organisation
Meca-Ouest
Address
15 RUE MARCEL LEBOURGEOIS ZONE INDUSTRIELLE NO.1 LA FREMONDIERE, 61300 L'AIGLE, France
EU Contribution
€434 619

Technologies

Technology Theme
Computer-aided design and engineering
Technology
Improvement of transition-prediction tools for future laminar flow aircraft
Development phase
Research/Invention

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