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15 projets européens trouvés

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 TERMINÉ 

Regional turboprop loads control through active and passive technologies (RELOAD)

Date du début: 1 déc. 2015, Date de fin: 30 sept. 2018,

A number of active and passive Loads Control and Alleviation concepts and technologies will be proposed, developed and evaluated. Aerodynamic design of an innovative spoiler will be undertaken, followed by a detailed aerodynamic characterisation of the spoiler and aileron capability for active loads control alleviation, conducted by means of CFD simulations and Wind Tunnel Tests. Novel passive loa ...
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 2

 TERMINÉ 

"""2nd Generation Active Wing“ – Active Flow- Loads & Noise control on next generation wing" (AFLONEXT)

Date du début: 1 juin 2013, Date de fin: 31 mai 2018,

AFLoNext is a four year EC L2 project with the objective of proving and maturing highly promising flow control technologies for novel aircraft configurations to achieve a quantum leap in improving aircraft’s performance and thus reducing the environmental footprint. The project consortium is composed by forty European partners from fifteen countries. The work has been broken down into seven work p ...
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 41

 TERMINÉ 

Experimental and Numerical Investigation of Turbulent Boundary Layer Effects on Noise Propagation in High Speed Conditions (ENITEP)

Date du début: 1 déc. 2012, Date de fin: 31 mai 2016,

...al acoustic data to validate and develop numerical simulation methods in order to better understand the complex phenomena of noise transmission from Contra-rotating Open Rotor engines (CROR) into the aircraft cabin at cruise conditions.The research will utilise a significant number of existing test components and acoustic instrumentation to maximise the quantity of unique experimental data obtaine ...
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 2

 TERMINÉ 

Combined morphing assessment software using flight envelope data and mission based morphing prototype wing development (CHANGE)

Date du début: 1 août 2012, Date de fin: 31 déc. 2015,

"Morphing in aircrafts has been studied and used throughout recent time in order to increase their flight envelope. This characteristic is of the upmost importance in order to offer a greater efficiency, versatility and performance during the assigned mission. Moreover an aircraft with the capability to adapt itself to each given situation is prone to achieve positive results to a range of differe ...
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 9

 TERMINÉ 

Buffet Control of Transonic Wings (BUCOLIC)

Date du début: 1 oct. 2013, Date de fin: 30 juin 2015,

"The aim of this work programme is to develop a capability to understand and predict transonic buffet on wings fitted with buffet control devices.Wind tunnel tests will be performed on a half model with buffet control devices fitted to measure dynamic flow characteristics during buffet onset.Unsteady RANS and DES CFD calculations will be carried out, validated against the wind tunnel data. The CF ...
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 2

 TERMINÉ 

Model Design and Manufacturing of the Turbofan Configuration for Low Speed Aerodynamic and Acoustic Testing (LOSPA)

Date du début: 1 nov. 2011, Date de fin: 31 déc. 2014,

...ber of steady and unsteady probes will be installed in the model. Kulites ® will be mounted in the thin nacelle and empennage. These will be supplemented by gauges on the empennage to measure loads.Aircraft Research Association (ARA) proposes to apply its extensive experience in wind tunnel model design and manufacture. ARA will lead the programme of work with manufacturing support provided by F ...
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 2

 TERMINÉ 

"Wind Tunnel Model Design with Active Flow Control, for Low Speed Test" (DEAFCON)

Date du début: 1 juil. 2013, Date de fin: 31 déc. 2014,

"The original requirement covered by this DEAFCON proposal was for the detailed design of two low speed half models, with a fully pressure plotted low sweep and high sweep wing respectivelyRemovable and variable Leading Edge, Trailing Edge and Wing Tip devices were to be included, and the main element of innovation and learning for ARA would have been the integration of some form of Active Flow Co ...
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 1

 TERMINÉ 

Contribution to Analysis of Rotor Hub Drag Reduction (CARD)

Date du début: 1 nov. 2010, Date de fin: 31 oct. 2014,

"A major source of helicopter drag, about 30% of the total, is from the rotor hub. It is important that the drag generated by a helicopter, and hence emissions, is reduced. This research programme is to be undertaken to investigate this subject and investigate potential techniques to achieve reductions in hub drag. A wind tunnel test programme is to be carried out to provide a large, high-quali ...
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 3

 TERMINÉ 

Industrialisation of High-Order Methods – A Top-Down Approach (IDIHOM)

Date du début: 1 oct. 2010, Date de fin: 31 mars 2014,

"The proposed IDIHOM project is motivated by the increasing demand of the European aerospace industries to advance their CFD-aided design procedure and analysis by using accurate and fast numerical methods, so-called high-order methods. They will be assessed and improved in a top-down approach by utilising industrially relevant complex test cases, so-called application challenges in the general ar ...
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 21

 TERMINÉ 

Control and Alleviation of Loads in Advanced Regional Turbo Fan Configurations (CLAReT)

Date du début: 28 janv. 2012, Date de fin: 27 sept. 2013,

...e orientation and twist throughout the flight envelope whilst also providing a passive gust loads alleviation capability. A CFD based aerodynamic design of the device applied on a baseline Turbo-Fan Aircraft configuration model will be undertaken, followed by a preliminary lay-out definition of the structure and actuation system required for the device. Detailed parametric studies will then be p ...
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 4

 TERMINÉ 

Smart High Lift Devices for Next Generation Wings (SADE)

Date du début: 1 mai 2008, Date de fin: 31 oct. 2012,

"All aerodynamic concepts for significant reduction of drag such as laminarisation require slim high-aspect-ratio wings. However, state-of-the-art high lift systems will suffer from the reduced construction space and do not cope with the required surface quality. Thus, SADE (Smart High Lift Devices for Next Generation Wings) develops suitable 'morphing' high lift devices: The seamless 'smart leadi ...
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 13

 TERMINÉ 

Collaborative & Robust Engineering using Simulation Capability Enabling Next Design Optimisation (CRESCENDO)

Date du début: 1 mai 2009, Date de fin: 31 oct. 2012,

...y contributing significantly to the fulfilment of three specific targets of the aeronautical industry’s Strategic Research Agenda. CRESCENDO will develop the foundations for the Behavioural Digital Aircraft (BDA), taking experience and results from VIVACE, and integrating these into a federative system and building the BDA on top of them. Main components of the BDA are: the Model Store, the Simula ...
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 59

 TERMINÉ 

INNOVATIVE DESIGN OF HUBS AND PROPELLERS (IDOHAP)

Date du début: 1 janv. 2010, Date de fin: 30 juin 2011,

"The IDOHAP proposal is for the detailed design of two CROR models to be installed on an existing wind tunnel test rig. Each model to comprise a pair of hubs and associated propeller blades. This work will be achieved using design engineers experienced in the design of complex wind tunnel models and associated test rigs, using the Catia V5 (V16) software package. These model designs are required f ...
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 1

 TERMINÉ 

Development of Synthetic Jet Actuator Hardware for the Green Regional Aircraft Low Noise Configuration (VELOCIRAPTOR)

Date du début: 15 févr. 2010, Date de fin: 14 avr. 2011,

...ramme in which this capability was demonstrated, the University of Manchester (UoM) proposes to develop such a system in conjunction with the manufacturing and windtunnel operational expertise of the Aircraft Research Association (ARA). The proposal has the potential to considerably advance the state of the art in SJA technology through use of a novel scalable cantilever based electro-mechanical c ...
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 2

 TERMINÉ 

Acoustic Design Of High-lift Architectures (ADOCHA)

Date du début: 1 janv. 2010, Date de fin: 30 nov. 2010,

"Regulation of the sound production of aircraft is becoming stricter, in part due to an increase in the noise generated due to the rising numbers and size of aircraft. As a result identification and reduction of the major sources of sound, particularly in the take-off and landing phases when the aircraft is close to population centres, is paramount. High lift devices, particularly during the landi ...
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 2