Predictive Numerical Study of Cambered Morphing A320 High-Lift Configuration Based on Electro-Mechanical Actuators

Aiaa Aviation 2021 Forum

Chouippe

Vos

et al. 2021

This study investigates the physical mechanisms of the use of Active Flow Control (AFC) associated with morphing through cambering approach in a high-lift wing-flap system. Results of high-fidelity numerical simulations are examined at high Reynolds number (Re/c) of 4.6 Million. Adapted turbulence models are used to capture the flow separation and the development of coherent structures. Different approaches of AFC are proposed to suppress the flow separation located approximately at 60% of the cambered flap's chord. The present study focuses on AFC using steady continuous jet, unsteady valves or oscillators (pulsed blowing) and more precisely the Zero Net Mass Flux (synthetic jet) with the blowing-suction approach. The AFC at an optimal velocity and frequency of actuation enabled an enforcement of the flow re-attachment and a delay of the flow separation. The minimum jet velocity and a feasible vibration frequency are discussed providing a practically complete control of the separation regarding the high deflection angle and cambering dimensions. As a main result of the study, the pressure distribution is enhanced over both wing-flap surfaces, adverse pressure gradients are suppressed and the re-attachment of the boundary layer is obtained. These results have the potential to increase significantly the aerodynamic efficiency of aircraft during the take-off and landing phases.

“…High-frequency and low-amplitude of deformation using the equation 1 has been studied in [23] . Equation 2 deals with the cambering approach( [24]). Fig.…”

Section: Morphing Boundary Conditionmentioning

confidence: 99%

Section: Morphing Boundary Conditionmentioning

confidence: 99%

Unsteady CFD simulations for Active Flow Control

Aiaa Aviation 2021 Forum

Chouippe

Vos

et al. 2021

“…Montazer et al [10] optimized the position and frequency of a synthetic jet using the Response Surface Methodology. More recently, the authors investigated two-dimensional active control using different blowing strategies similar to piezo-actuators embedded in the flap of a high-lift system [11][12][13]. The active flow control was combined with a morphing flap through cambering, which led to large flow separations on the suction side of the flap and a decrease in aerodynamic efficiency.…”

Section: Introductionmentioning

confidence: 99%

Optimization of Synthetic jet to enhance the aerodynamic performance of a VTOL aircraft at real flight conditions

Truong

AIAA SCITECH 2023 Forum

Hoarau

et al. 2023

The study described in this paper was conducted as part of the European Funded CleanSky2 project AFC4TR (Active Flow Control for Tilt-Rotor aircraft). High-Fidelity numerical simulations were made to study various approaches of using Active Flow Control (AFC) actuators to delay flow separation at near stall conditions of the Next Generation Civil Tilt Rotor (NGCTR) VTOL aircraft with a tilted nacelle used during take-off and landing. The study revealed that for this configuration the flow separations travel in the spanwise direction starting from the middle of the wing. Various flow control strategies using Zero Net Mass Flux (ZNMF) actuators (synthetic jets) were then tested. Different number of actuators were integrated on * Postdoc,

“…More recently, we studied two-dimensional active control using different strategies of steady blowing, transient blowing and blowing-suction method similar as piezo-actuators embedded inside the flap of a high-lift system [12]. The AFC was coupled with a morphing flap [13] using the cambering approach [14][15][16]. The concept of cambering lead to large flow separations on the suction side of the flap, resulting in an important increase of the drag and decrease of the aerodynamic efficiency.…”

Section: Introductionmentioning

confidence: 99%

Flow analysis around a VTOL aircraft near stall conditions and application of Active Flow Control to enhance the aerodynamic performances at real flight conditions

Truong

AIAA AVIATION 2022 Forum

Chouippe

et al. 2022

This paper discusses the physical dynamics of the use of the Active Flow Control (AFC) actuators embedded in a Vertical Take-Off and Landing (VTOL) aircraft. Results of High-Fidelity numerical simulations are examined at near stall conditions. Different approaches of AFC are proposed to suppress the flow separation at these conditions. First the flow around the VTOL aircraft at high angle of attack in the take-off and landing configurations in real flight conditions at high Reynolds number are examined, then different flow control strategies are investigated. It was found that at these flow condition a flow separation travels along the spanwise direction in the near trailing-edge region of the wing with additional corner vortices between the wing-nacelle and the wing-fuselage junctions. Zero Net Mass Flux (ZNMF) actuators, also called synthetic jets, were then used for Active Flow Control. It was found that these ZNMF devices, when operating at the optimal blowing velocity and activation frequency, and when placed at the correct location enable the flow to re-attach and to delay the flow separation, resulting in an increase in aerodynamic efficiency of the aircraft. This work presented in this paper has been carried out in the context of the European project CleanSky2 Active Flow Control for TiltRotor aircraft (AFC4TR), Grant Agreement 886718.