Stereo particle image velocimetry measurements of perpendicular blade–vortex interaction over an oscillating airfoil

Zanotti, Alex; Ermacora, M.; Campanardi, G.; Gibertini, G.

doi:10.1007/s00348-014-1811-8

Cited by 25 publications

(15 citation statements)

References 20 publications

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“…Therefore, the spatial resolution of the velocity measurement points was about 2 mm. The accuracy of the present PIV measurement can be estimated considering a maximum displacement error of 0.1 px (25) . Thus, taking into account the employed pulse-separation time and the optical magnification (26) , the maximum in-plane velocity components error was about 0.2 m/s.…”

Section: Piv Set-upmentioning

confidence: 99%

Experimental investigation of a helicopter rotor with Gurney flaps

et al. 2017

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The present work describes an experimental activity carried out to investigate the performance of Gurney flaps on a helicopter rotor model in hovering. The four blades of the articulated rotor model were equipped with Gurney flaps positioned at 95% of the aerofoil chord, spanning 14% of the rotor radius. The global aerodynamic loads and torque were measured for three Gurney flap configurations characterised by different heights. The global measurements showed an apparent benefit produced by Gurney flaps in terms of rotor performance with respect to the clean blade configuration. Particle image velocimetry surveys were also performed on the blade section at 65% of the rotor radius with and without the Gurney flaps. The local velocity data was used to complete the characterisation of the blade aerodynamic performance through the evaluation of the sectional aerodynamic loads using the the control volume approach

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Section: Piv Set-upmentioning

confidence: 99%

Experimental investigation of a helicopter rotor with Gurney flaps

et al. 2017

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“…The PIV system was set up to measure the three velocity components on longitudinal X -Z plane windows at different span-wise locations of the model. This technique enabled reconstruction of the average three-dimensional flow field over a volume of interest, as performed in the work by Zanotti et al (16) . A set of 100 image pairs was acquired for each measurement plane.…”

Section: Stereo Piv Set-upmentioning

confidence: 99%

Wind-tunnel tests of a heavy-class helicopter optimised for drag reduction

et al. 2016

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Wind-tunnel tests of a heavy-class helicopter model were carried out to evaluate the effectiveness of several components optimised for drag reduction by computational fluid dynamics analysis. The optimised components included different hub-cap configurations, a fairing for blade attachments and the sponsons. Moreover, the effects of vortex generators positioned on the back ramp were investigated. The optimisation effect was evaluated by comparison of the drag measurements carried out for both the original and the optimised helicopter configurations. The comprehensive experimental campaign involved the use of different measurement techniques. Indeed, pressure measurements and stereo particle image velocimetry surveys were performed to achieve a physical insight about the results of load measurements. The test activity confirms the achievement of an overall reduction of about 6% of the original model drag at cruise attitude

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“…The image pairs were post-processed using the multigrid interrogation algorithm [12] leading to a resolution of a measurement point every 7 mm. The accuracy of the present PIV measurements can be estimated considering a maximum displacement error of 0.1 pixels [13]. Thus, taking into account the employed pulse-separation time and the optical magnification [14], the maximum in-plane velocity components error of the present measurements is about 0.07 m/s.…”

Section: Piv Set Upmentioning

confidence: 99%

Experimental investigation of the unsteady aerodynamics of FOWT through PIV and hot-wire wake measurements

Bayati

Bernini

Zanotti

et al. 2018

J. Phys.: Conf. Ser.

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Abstract. This work presents a selected set of results from an extensive experimental campaign aimed at characterizing the wake aerodynamics of a floating offshore wind turbines (FOWT) in dynamic conditions. The campaign was carried out in the Politecnico di Milano 14m x 4m atmospheric boundary layer test section, under UNAFLOW project (UNsteady Aerodynamics of FLoating Wind turbines). Wake measurements were carried out either through hot-wire anemometers with a traversing system as well as through Particle Image Velocimetry (PIV) technique. A 1/75 scale model of the DTU 10 MW reference wind turbine was adopted, which was mounted on a hydraulically actuated mechanism imposing sinusoidal surge motion at different frequencies and amplitudes, and for different tip speed ratios λ. Selected results are reported with the aim of giving a first interpretation of the novel set of measurements, also completing previous measurements conducted by the authors, to put the basis of a more comprehensive understanding of unsteady aerodynamics of FOWT for control and wind farm purposes.

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Stereo particle image velocimetry measurements of perpendicular blade–vortex interaction over an oscillating airfoil

Abstract: Access to the published version may require subscription.When citing this work, cite the original published paper.

Cited by 25 publications

References 20 publications

Experimental investigation of a helicopter rotor with Gurney flaps

Experimental investigation of a helicopter rotor with Gurney flaps

Wind-tunnel tests of a heavy-class helicopter optimised for drag reduction

Experimental investigation of the unsteady aerodynamics of FOWT through PIV and hot-wire wake measurements

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