PIV measurements of the asymmetric wake of a two dimensional heaving hydrofoil

Ellenrieder, Karl D. von; Pothos, Stamatios

doi:10.1007/s00348-007-0430-z

Cited by 74 publications

(46 citation statements)

References 21 publications

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“…[19][20][21][22] For simulating airfoil heaving problems, the current scheme is further validated by comparing velocity As stated earlier, this location of the maximum velocity in the wake will be used to determine the deflection angle of the asymmetric wake. 11,15,16 The sinusoidal heaving motion of a symmetric airfoil, a NACA0012 airfoil, is specified as…”

Section: Methodsmentioning

confidence: 99%

“…The Strouhal number, which is the product of reduced frequency and dimensionless heaving magnitude, is a considered a primary factor that influences the wake of a heaving airfoil. 6,7,9,10,12,15 The computational domain size selected for this study is 19.2 × 12.8, shown in Fig. 2.…”

Section: Methodsmentioning

confidence: 99%

“…10,15 The current study is the first that has investigated the effect of amplitude and frequency individually on the wake deflection angle. A general consensus in the previous work 7,10,12,15 was that a larger value of V p is related to a larger deflection angle. However, it was reported 6, 7 that in some cases, a flow with larger Strouhal number might not show any wake deflection.…”

Section: A Effects Of the Strouhal Number Versus The Individual Effementioning

confidence: 99%

“…6, with omitted curves for velocity profiles, will be frequently employed in the following discussion to compare the wake deflection angles. Figure 7 shows that the deflection angle increases as V p increases by increasing the reduced frequency, k, at a fixed heaving amplitude 10,15 (h = 0.12 and 0.16, respectively). In this case, the magnitude of maximum downstream velocity also increases, as the symbols on curves with the same line type (solid or dotted-dashed, indicating h = 0.12 and 0.16, respectively) from the same location increase their magnitudes in the abscissa direction.…”

Section: A Effects Of the Strouhal Number Versus The Individual Effementioning

confidence: 99%

“…For quantifying the deflection angle, the location of the maximum streamwise velocity in the wake was used to determine the deflection angle. 11,15,16 Godoy-Diana et al 17 proposed a vortex dipole model to provide a quantitative prediction of the symmetry breaking wake based on two consecutive counter-rotating vortices in the wake. A symmetry-breaking criterion based on the phase velocity and idealized self-advection velocity of vortex dipole was discussed.…”

Section: Introductionmentioning

confidence: 99%

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Study of mechanisms and factors that influence the formation of vortical wake of a heaving airfoil

Zheng¹,

Wei²

2012

Physics of Fluids

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A direct numerical simulation investigation of the synthetic jet frequency effects on separation control of low-Re flow past an airfoil Phys. Fluids 27, 055101 (2015) A two-dimensional numerical study is performed to investigate the relation between the direction of a deflected wake and the vortex pairing mechanisms. The deflection angle can be correlated with two effective phase velocities defined to represent the trends of symmetry breaking and symmetry holding, respectively. The deflection angle increases with the strength of the vortex pairs, which is associated with the heaving amplitude, frequency, and the free stream Reynolds number. Furthermore, not only the influence of Strouhal number but also those of the two heaving motion componentsamplitude and frequency -are studied individually under different Reynolds numbers. The study shows that the deflection angle consistently increases with the difference between the symmetry-breaking phase velocity and symmetry-holding phase velocity. C 2012 American Institute of Physics. [http://dx

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Section: Methodsmentioning

confidence: 99%

Section: Methodsmentioning

confidence: 99%

Section: A Effects Of the Strouhal Number Versus The Individual Effementioning

confidence: 99%

Section: A Effects Of the Strouhal Number Versus The Individual Effementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Study of mechanisms and factors that influence the formation of vortical wake of a heaving airfoil

Zheng¹,

Wei²

2012

Physics of Fluids

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Flow control over a NACA 0012 airfoil using dielectric-barrier-discharge plasma actuator with a Gurney flap

et al. 2012

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Flow control study of a NACA 0012 airfoil with a Gurney flap was carried out in a wind tunnel, where it was demonstrated that a dielectric-barrier-discharge (DBD) plasma actuator attached to the flap could increase the lift further, but with a small drag penalty. Timeresolved PIV measurements of the near-wake region indicated that the plasma forcing shifted the wake downwards, reducing its recirculation length. Analysis of wake vortex dynamics suggested that the plasma actuator initially amplified the lower wake shear layer by adding momentum along the downstream surface of the Gurney flap. This enhanced mutual entrainment between the upper and lower wake vortices, leading to an increase in lift on the airfoil.

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Analysis of three-dimensional attributes and flow intake for an oscillating cantilever

Eastman

Kimber

2014

Exp Fluids

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PIV measurements of the asymmetric wake of a two dimensional heaving hydrofoil

Cited by 74 publications

References 21 publications

Study of mechanisms and factors that influence the formation of vortical wake of a heaving airfoil

Study of mechanisms and factors that influence the formation of vortical wake of a heaving airfoil

Flow control over a NACA 0012 airfoil using dielectric-barrier-discharge plasma actuator with a Gurney flap

Analysis of three-dimensional attributes and flow intake for an oscillating cantilever

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