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AFLONEXT - Active Flow_LOads and Noise control on neXT generation wing

Obiettivo

The AFLoNext project is based on six Technology Streams, which cluster the targeted technologies and their associated contributions to advanced aircraft performance as follows:

TS-1: Hybrid Laminar Flow Control (HLFC) technology applied on fin and wing for friction drag reduction and thus performance increase in cruise conditions.

TS-2: Flow control technologies to enable more aggressive outer wing design for novel aircraft configurations, thereby improving the performance and the loads situation in low and high speed conditions.

TS-3: Technologies for local flow separation control applied in wing/pylon junction to improve the performance and loads situation mainly in take-off and landing conditions.

TS-4: Technologies to control the flow conditions on wing trailing edges thereby improving the performance and loads situation in the whole operational domain.

TS-5: Technologies to mitigate airframe noise during landing generated on flap and undercarriage and through mutual interaction of both.

TS-6: Technologies to mitigate/control vibrations in the undercarriage area, which are caused by highly unsteady or inhomogeneous inflow conditions in take-off and landing conditions.

AFLoNext aims to prove the engineering feasibility of the HLFC technology for drag reduction on fin in flight test, and on wing by means of large scale ground testing. To improve aircraft performance along the whole flight regime, locally applied active flow control technologies on wing and wing/pylon junction are qualified in wind tunnels or by means of lab-type demonstrators.

Attività nel progetto CIRA

CIRA contribution in AFLoNext deploys on Technology Streams (TS) 1-4 with the following activities:

TS-1:  Application of laminar-turbulent transition models (boundary layer stability) to predict the laminar flow extension achieved thanks to the distributed (HLFC) suction in the wing leading edge region.

Aero-design (CFD-based) of a Krueger flap at the leading edge of a HLFC wing, by including integration constraints due to the presence of other systems at the leading edge.

Prediction of water impingement and ice accretion on the HLFC wing, for the sizing of the Ice Protection System (IPS) based on hot air blowing at the leading edge.

Contribution to the design of a Ground Based Demonstrator, to be used for the wind tunnel testing of the designed IPS. CFD-based aero-design of the wing-box and the rear adjustable flap.

Icing Wind Tunnel testing of a 2.25 x 2 meters Ground Demonstrator, equipped with IPS, Krueger flap device, and all subsystems.

TS-2: Unsteady aerodynamics and active flow control (URANS/CFD) simulation of steady suction, steady blowing and synthetic jets actuators installed at the outer wing of a commercial transport aircraft (Airbus A330 type) at low-speed/high-lift conditions.

TS-3: Unsteady aerodynamics and active flow control (URANS/CFD) simulation of steady blowing and pulsed jets actuators installed at the wing/engine-pylon junction of a commercial transport aircraft (Airbus A330 type) at low-speed/high-lift conditions.

TS-4: Steady aerodynamics and aero-optimization (RANS/CFD) of a multi-functional fluidic Gurney flap, for buffet control purposes at transonic conditions and high-lift performance improvement in the low speed regime.

Programma

​ EC in the frame of FP7 Collaborative Projects – Large Scale (L2).  

  • data inizio: Saturday, June 1, 2013
  • durata: 60.00
Wednesday, February 8, 2017
155
Thursday, February 9, 2017
AFLONEX
Fluid Mechanics
The AFLoNext project aims at 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.
Computational Fluid Dynamics, Unsteady Aerodinamics, Aeronautical Propulsion Integration, Airflow Control, Wind Tunnel Measuring Techniques
Icing Wind Tunnel (IWT), Scientific computing systems
http://www.aflonext.eu/

 

 

AFLONEXT - Active Flow_LOads and Noise control on neXT generation wing<img alt="" src="http://webtest.cira.it/PublishingImages/AFLONEXT.png" style="BORDER:0px solid;" />https://www.cira.it/en/aeronautics/fixed-wing-air-vehicle/aflonex/AFLONEXT - Active Flow_LOads and Noise control on neXT generation wingAFLONEXT - Active Flow_LOads and Noise control on neXT generation wing<p></p><p>The AFLoNext project is based on six Technology Streams, which cluster the targeted technologies and their associated contributions to advanced aircraft performance as follows:</p><p>TS-1: Hybrid Laminar Flow Control (HLFC) technology applied on fin and wing for friction drag reduction and thus performance increase in cruise conditions.</p><p>TS-2: Flow control technologies to enable more aggressive outer wing design for novel aircraft configurations, thereby improving the performance and the loads situation in low and high speed conditions.</p><p>TS-3: Technologies for local flow separation control applied in wing/pylon junction to improve the performance and loads situation mainly in take-off and landing conditions.</p><p>TS-4: Technologies to control the flow conditions on wing trailing edges thereby improving the performance and loads situation in the whole operational domain.</p><p>TS-5: Technologies to mitigate airframe noise during landing generated on flap and undercarriage and through mutual interaction of both.</p><p>TS-6: Technologies to mitigate/control vibrations in the undercarriage area, which are caused by highly unsteady or inhomogeneous inflow conditions in take-off and landing conditions.</p><p>AFLoNext aims to prove the engineering feasibility of the HLFC technology for drag reduction on fin in flight test, and on wing by means of large scale ground testing. To improve aircraft performance along the whole flight regime, locally applied active flow control technologies on wing and wing/pylon junction are qualified in wind tunnels or by means of lab-type demonstrators.</p><p>​ EC in the frame of FP7 Collaborative Projects – Large Scale (L2).  </p><p></p><p>CIRA contribution in AFLoNext deploys on Technology Streams (TS) 1-4 with the following activities:</p><p><strong>TS-1</strong>:  Application of laminar-turbulent transition models (boundary layer stability) to predict the laminar flow extension achieved thanks to the distributed (HLFC) suction in the wing leading edge region.</p><p>Aero-design (CFD-based) of a Krueger flap at the leading edge of a HLFC wing, by including integration constraints due to the presence of other systems at the leading edge.</p><p>Prediction of water impingement and ice accretion on the HLFC wing, for the sizing of the Ice Protection System (IPS) based on hot air blowing at the leading edge.</p><p>Contribution to the design of a Ground Based Demonstrator, to be used for the wind tunnel testing of the designed IPS. CFD-based aero-design of the wing-box and the rear adjustable flap.</p><p style="text-align:justify;">Icing Wind Tunnel testing of a 2.25 x 2 meters Ground Demonstrator, equipped with IPS, Krueger flap device, and all subsystems.</p><p><strong>TS-2</strong>: Unsteady aerodynamics and active flow control (URANS/CFD) simulation of steady suction, steady blowing and synthetic jets actuators installed at the outer wing of a commercial transport aircraft (Airbus A330 type) at low-speed/high-lift conditions.</p><p><strong>TS-3</strong>: Unsteady aerodynamics and active flow control (URANS/CFD) simulation of steady blowing and pulsed jets actuators installed at the wing/engine-pylon junction of a commercial transport aircraft (Airbus A330 type) at low-speed/high-lift conditions.</p><p><strong>TS-4</strong>: Steady aerodynamics and aero-optimization (RANS/CFD) of a multi-functional fluidic Gurney flap, for buffet control purposes at transonic conditions and high-lift performance improvement in the low speed regime.</p>2013-05-31T22:00:00Z60.0000000000000

 Media gallery

 

 

Simulazioni CFD/RANS – TS2https://www.cira.it/PublishingImages/Forms/DispForm.aspx?ID=1043Simulations CFD/RANS – TS2Simulazioni CFD/RANS – TS2Imagehttps://www.cira.it/PublishingImages/OUTER-WING_NO-AFC.png
Simulazioni CFD/RANS – TS2https://www.cira.it/PublishingImages/Forms/DispForm.aspx?ID=1044Simulations CFD/RANS – TS2Simulazioni CFD/RANS – TS2Imagehttps://www.cira.it/PublishingImages/OUTER-WING_NO-AFC2.png
Griglia computazionale – TS2https://www.cira.it/PublishingImages/Forms/DispForm.aspx?ID=1045Griglia computazionale attorno alla zona del tip alare di un velivolo da trasporto commerciale.Griglia computazionale – TS2Imagehttps://www.cira.it/PublishingImages/OUTER-WING_SLOT.png
Simulazioni CFD di sistemi di controllo del flusso – TS3https://www.cira.it/PublishingImages/Forms/DispForm.aspx?ID=1048Simulazioni CFD di sistemi di controllo del flusso – TS3Imagehttps://www.cira.it/PublishingImages/WING-ENGINE_CFD.png
Modellazione CAD/CFD – TS3https://www.cira.it/PublishingImages/Forms/DispForm.aspx?ID=1049Modellazione CAD/CFD – TS3Imagehttps://www.cira.it/PublishingImages/WING-ENGINE_GRID.png
PREDIZIONE GHIACCIO – TS1https://www.cira.it/PublishingImages/Forms/DispForm.aspx?ID=1040Predizione dell’accumulo acqua, accrescimento ghiaccio e Potenza termica per anti-icingPREDIZIONE GHIACCIO – TS1Imagehttps://www.cira.it/PublishingImages/ICE2.png
Design CFD di un dispositivo da bordo d’uscita multi-funzionale (alta velocità) – TS4https://www.cira.it/PublishingImages/Forms/DispForm.aspx?ID=1046Design CFD di un dispositivo da bordo d’uscita multi-funzionale (alta velocità) – TS4Imagehttps://www.cira.it/PublishingImages/TED-1.png
Design CFD di un dispositivo da bordo d’uscita multi-funzionale https://www.cira.it/PublishingImages/Forms/DispForm.aspx?ID=1047Design CFD di un dispositivo da bordo d’uscita multi-funzionale Imagehttps://www.cira.it/PublishingImages/TED-2.png

 Activities