Simulation and optimization of stall control for an airfoil with a synthetic jet

Duvigneau, Régis; Visonneau, Michel

doi:10.1016/j.ast.2006.01.002

Cited by 44 publications

(22 citation statements)

References 16 publications

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“…One can remark that the DBD actuation seems contribute to only one flow structure contrary to flow control performed by synthetic jets. Indeed, it was experimentally [44] and numerically [45] demonstrated that the lift increase observed for stall control by synthetic jet is due to the creation of two or three vortices convected along the suction side of a NACA 0015 airfoil. Phase-averaged PLIF visualisations have also demonstrated that the coherent structures responsible for the apparent reattachment could coalesce to form a single, more intense vortex synthetic [46].…”

Section: Reattachment Process By Non-thermal Plasma Actuatormentioning

confidence: 99%

On the Vortex Dynamic of Airflow Reattachment Forced by a Single Non-thermal Plasma Discharge Actuator

Bénard

Moreau

2011

Flow Turbulence Combust

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Commercial and military aircrafts or miniature aerial vehicles can suffer from massive flow separation when high angles of attack are required. Single dielectric barrier discharge (DBD) actuators have demonstrated their capability of controlling such a separated flow at low external velocity. However, the processes resulting in the improvement of the flight performances remain unclear. In the present study, the reattachment process along the suction side of a NACA 0015 placed at an angle of attack of 16 • is experimentally investigated for an external velocity of 20 m/s (Re = 260,000). A single DBD actuator is mounted at the leading edge of the model. The velocity fields above the suction side of the airfoil are measured by a high-speed acquisition system (3 kHz). The results indicate that the baseline flow presents shed vortices that form at the leading edge and linearly grow along the free shear layer axis. This vortex shedding is organized and exhibits a specific frequency of about 90 Hz. The continuous actuation produces a partial flow reattachment up to 70% of the chord length. Temporal cross-correlation function indicates the presence of a vortex shedding at the trailing edge of the controlled flow. Finally, the temporal analysis demonstrates that the reattachment process requires 50 ms to reach a stabilized attached flow. The time-resolved analysis of the reattachment suggests that the actuation by plasma discharge acts as a catalyser by reinforcing one of the coherent flow structures already existing in the natural flow.

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Section: Reattachment Process By Non-thermal Plasma Actuatormentioning

confidence: 99%

On the Vortex Dynamic of Airflow Reattachment Forced by a Single Non-thermal Plasma Discharge Actuator

Bénard

Moreau

2011

Flow Turbulence Combust

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“…Among the many optimization strategies available (e.g., finite difference or adjoint-based gradients and descent, simulatedannealing [41], simplex or multidirectional search [28]), a derivativefree, genetic algorithm (see Fig. 2 for an overview), GADO [42], was preferred for the following reasons:…”

Section: Optimizermentioning

confidence: 99%

“…As a possible answer [28,29], a completely automated, surrogate-based optimization [30,31] algorithm was developed and applied to the design of a two-dimensional high-lift system with a conventional slotted slat and a simply hinged, slotless flap. The process will now be described in detail and results for a continuously blowing slot will be presented.…”

mentioning

confidence: 99%

Simulation and Optimization of Flow Control Strategies for Novel High-Lift Configurations

Meunier

2009

AIAA Journal

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A kriging-based optimization algorithm is presented and applied to the design of a novel high-lift airfoil with a simply hinged, slotless flap and equipped with fluidic flow control. The position, orientation, and continuous-blowing characteristics of the actuator are set as design variables for the maximization of lift in landing conditions. Comparisons with a fully slotted reference configuration are presented and conclusions are drawn. In particular, it is found that a careful parameterization of the jet is capable of an efficient control strategy and leads to a complete reattachment of the flap flow, with considerable gains in lift and aerodynamic efficiency. A functional analysis of variance demonstrates the possibility of a dimensional reduction in the problem formulation and allows for a more in-depth analysis of the mechanisms governing separation management and alleviation in that particular case.freestream Mach number N = number of samples P = number of variables Re j = l ref -based Reynolds number VR = jet to local isentropic velocity ratio V inj = injection velocity V isentropic = isentropic boundary velocity V x = streamwise velocity V 1 = freestream velocity x inj = injection abscissa y = normalized first cell height = angle of attack = boundary-layer thickness flap = flap deflection angle inj = injection angle

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“…The actuation frequencies are in the kHz range and are related to the airflow speed [10]. Most of the literature focuses on fixed wind tunnel test [10] but simulations show a potential increase in the maximum lift of an airfoil by 34% with an increase in the maximum stall angle of a profile [17]. These characteristics make synthetic jets system very promising for improving the characteristics of a profile for helicopter applications.…”

Section: Active Flow Controlmentioning

confidence: 99%

Smart Actuation for Helicopter Rotorblades

Paternoster¹,

Loendersloot²,

Boer³

et al. 2012

Smart Actuation and Sensing Systems - Recent Advances and Future Challenges

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Simulation and optimization of stall control for an airfoil with a synthetic jet

Cited by 44 publications

References 16 publications

On the Vortex Dynamic of Airflow Reattachment Forced by a Single Non-thermal Plasma Discharge Actuator

On the Vortex Dynamic of Airflow Reattachment Forced by a Single Non-thermal Plasma Discharge Actuator

Simulation and Optimization of Flow Control Strategies for Novel High-Lift Configurations

Smart Actuation for Helicopter Rotorblades

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