Controlled transitory stall on a pitching airfoil using pulsed actuation

Woo, George T. K.; Glezer, Ari

doi:10.1007/s00348-013-1507-5

Cited by 13 publications

(2 citation statements)

References 23 publications

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“…Furthermore, they reported that a hydrogen/air mixture undergoing combustion in a 1 mL chamber results in an energy release of approximately 3.2 J, which is three orders of magnitude higher than the initial electrical energy input. Brzozowski et al [16] and Woo et al [17] tested this method on a stalled NACA 4415 under incompressible flow conditions and demonstrated a rapid increase in circulation in the experimental measurements. Woo et al [18] used this actuation for the rotorbody interaction and demonstrated a reduction in the aerodynamic drag of the fuselage.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study on Combustion-Driven Jet Actuation for Aerodynamic Control of Airfoil Flows

Kim,

Park,

Sohn

2023

Energies

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In this study, a numerical investigation is conducted on combustion-driven pulsed-jet actuation to control the flow around a lifting surface. Based on relevant experimental measurements and computations, high-speed jets are generated from the impulsive variation in pressure at the actuator boundary. A supersonic jet flow is momentarily generated by combustion in a reaction chamber of the actuator, and the flow interacts with the external flow around the lifting surface and alters the aerodynamic characteristics. The computational results indicate that the flow control performance of the jet actuation is significant at a high-incidence angle of attack, such as beyond the stall angle, whereas the impact is minimal at low angles of attack, such as in the linear lift region. Repetitive jet actuation can produce additional momentum to the external flow and alters the pressure distribution on the suction surface, particularly downstream of the actuator location. This pressure variation from the actuation yields an additional lift force on the lifting surface and reduces the amplitude of the aerodynamic moment at a given angle of attack, thus enhancing the aerodynamic performance of the airfoil.

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Section: Introductionmentioning

confidence: 99%

Numerical Study on Combustion-Driven Jet Actuation for Aerodynamic Control of Airfoil Flows

Kim,

Park,

Sohn

2023

Energies

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“…Using the right amplitude and frequency, the external boundary layer flow can be energized and controlled [4]. The energy transferred by pulsed air directly influences the flow behavior both locally (near the actuator) and globally (in the outer flow) [5,6]. Since the effect of transferring momentum and high energy flow to the surroundings is performed without mass transfer, SJs are often called Zero-Net Mass Flux (ZNMF) devices [7,8].…”

Section: Introductionmentioning

confidence: 99%

Towards Accurate Boundary Conditions for CFD Models of Synthetic Jets in Quiescent Flow

Matiz-Chicacausa

Mejia

2020

Energies

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In this paper, an accurate model to simulate the dynamics of the flow of synthetic jets (SJ) in quiescent flow is proposed. Computational modeling is an effective approach to understand the physics involved in these devices, commonly used in active flow control for several reasons. For example, SJ actuators are small; hence, it is difficult to experimentally measure pressure changes within the cavity. Although computational modeling is an advantageous approach, experiments are still the main technique employed in the study of SJs due to the lack of accurate computational models. The same aspect that represents an advantage over other techniques also represents a challenge for the computational simulations, such as capturing the unsteady phenomena, localized compressible effects, and boundary layer formation characteristic of this complex flow. One of the main challenges in the simulation of SJs is related to the fact that the spatial and temporal scales of the actuator and the corresponding flow control application differed in several orders of magnitude. Hence, in this study we focus on the use of Computational Fluid Dynamics (CFD) and Reduced Order Models (ROM) to develop an accurate yet low-cost model to capture the complexities of the flow of a SJ in quiescent flow. Numerical results show two possible paths for SJ modeling; (1) to obtain a boundary condition to predict velocity profile and jet formation from experimental data of diaphragm’s deformation; and, (2) to predict peak velocity at the jet’s outlet with a ROM approach and to use the physical details of the actuator to develop an accurate boundary condition for CFD. Both approaches are validated through experimental data available in the literature; good agreement between results from CFD, Lumped Element Model (LEM), and experimental data are achieved. Finally, it was concluded that the coupling between LEM and CFD is a novel and accurate approach, which improves CFD due to the advantages of LEM closing the gap between LEM’s lack of flow detail and CFD’s lack of geometrical/physical information of the actuator.

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Transient Process of Separation Control on a NACA0015 Airfoil

Siauw¹,

Bonnet²

2019

Advances in Effective Flow Separation Control for Aircraft Drag Reduction

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Controlled transitory stall on a pitching airfoil using pulsed actuation

Cited by 13 publications

References 23 publications

Numerical Study on Combustion-Driven Jet Actuation for Aerodynamic Control of Airfoil Flows

Numerical Study on Combustion-Driven Jet Actuation for Aerodynamic Control of Airfoil Flows

Towards Accurate Boundary Conditions for CFD Models of Synthetic Jets in Quiescent Flow

Transient Process of Separation Control on a NACA0015 Airfoil

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