Particle image velocimetry measurements of rigid and flexible rectangular wings undergoing main flapping motion in hovering flight

Srikanth Goli; Arnab Roy; Devendra Kumar Patel; Subhransu Roy

doi:10.1007/978-81-322-2743-4_135

Particle image velocimetry measurements of rigid and flexible rectangular wings undergoing main flapping motion in hovering flight

Srikanth Goli
, Arnab Roy^*
, Devendra Kumar Patel
, Subhransu Roy

^*Corresponding author for this work

Research output: Contribution to journal › Article › peer-review

7 Scopus citations

Abstract

The present work is focused on flow field behavior generated by rigid and flexible rectangular wings undergoing main flapping motion using two dimensional Particle Image Velocimetry (PIV). The experiments have been carried for an asymmetry one degree of freedom main flapping motion of both rigid and flexible low aspect ratio wings at 1 Hz flapping frequency in hovering flight mode (advanced ratio, J = 0) at zero geometric angle of attack, zero wing pitch angle and chord wise based Reynolds number of the order of 10⁴ along the wings spanwise direction at its mid chord to obtain instantaneous flow fields. The improved understanding of effect of wake capture, observation of spanwise flow on the wing, and formation-growth-diffusion of wingtip vortices have been achieved. Effect of wing flexibility on the flow field has been studied by comparing the flow field of both rigid and flexible rectangular wings undergoing main flapping motion.

Original language	English
Pages (from-to)	1411-1420
Number of pages	10
Journal	Lecture Notes in Mechanical Engineering
DOIs	https://doi.org/10.1007/978-81-322-2743-4_135
State	Published - 2017
Externally published	Yes

Bibliographical note

Publisher Copyright:
© Springer India 2017.

Keywords

Flapping motion
Flapping wing
Hovering flight
Micro air vehicle
Particle Image Velocimetry

ASJC Scopus subject areas

Automotive Engineering
Aerospace Engineering
Mechanical Engineering
Fluid Flow and Transfer Processes

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10.1007/978-81-322-2743-4_135

Cite this

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title = "Particle image velocimetry measurements of rigid and flexible rectangular wings undergoing main flapping motion in hovering flight",

abstract = "The present work is focused on flow field behavior generated by rigid and flexible rectangular wings undergoing main flapping motion using two dimensional Particle Image Velocimetry (PIV). The experiments have been carried for an asymmetry one degree of freedom main flapping motion of both rigid and flexible low aspect ratio wings at 1 Hz flapping frequency in hovering flight mode (advanced ratio, J = 0) at zero geometric angle of attack, zero wing pitch angle and chord wise based Reynolds number of the order of 104 along the wings spanwise direction at its mid chord to obtain instantaneous flow fields. The improved understanding of effect of wake capture, observation of spanwise flow on the wing, and formation-growth-diffusion of wingtip vortices have been achieved. Effect of wing flexibility on the flow field has been studied by comparing the flow field of both rigid and flexible rectangular wings undergoing main flapping motion.",

keywords = "Flapping motion, Flapping wing, Hovering flight, Micro air vehicle, Particle Image Velocimetry",

author = "Srikanth Goli and Arnab Roy and Patel, \{Devendra Kumar\} and Subhransu Roy",

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year = "2017",

doi = "10.1007/978-81-322-2743-4\_135",

language = "English",

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journal = "Lecture Notes in Mechanical Engineering",

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AU - Goli, Srikanth

AU - Roy, Arnab

AU - Patel, Devendra Kumar

AU - Roy, Subhransu

N1 - Publisher Copyright: © Springer India 2017.

PY - 2017

Y1 - 2017

N2 - The present work is focused on flow field behavior generated by rigid and flexible rectangular wings undergoing main flapping motion using two dimensional Particle Image Velocimetry (PIV). The experiments have been carried for an asymmetry one degree of freedom main flapping motion of both rigid and flexible low aspect ratio wings at 1 Hz flapping frequency in hovering flight mode (advanced ratio, J = 0) at zero geometric angle of attack, zero wing pitch angle and chord wise based Reynolds number of the order of 104 along the wings spanwise direction at its mid chord to obtain instantaneous flow fields. The improved understanding of effect of wake capture, observation of spanwise flow on the wing, and formation-growth-diffusion of wingtip vortices have been achieved. Effect of wing flexibility on the flow field has been studied by comparing the flow field of both rigid and flexible rectangular wings undergoing main flapping motion.

AB - The present work is focused on flow field behavior generated by rigid and flexible rectangular wings undergoing main flapping motion using two dimensional Particle Image Velocimetry (PIV). The experiments have been carried for an asymmetry one degree of freedom main flapping motion of both rigid and flexible low aspect ratio wings at 1 Hz flapping frequency in hovering flight mode (advanced ratio, J = 0) at zero geometric angle of attack, zero wing pitch angle and chord wise based Reynolds number of the order of 104 along the wings spanwise direction at its mid chord to obtain instantaneous flow fields. The improved understanding of effect of wake capture, observation of spanwise flow on the wing, and formation-growth-diffusion of wingtip vortices have been achieved. Effect of wing flexibility on the flow field has been studied by comparing the flow field of both rigid and flexible rectangular wings undergoing main flapping motion.

KW - Flapping motion

KW - Flapping wing

KW - Hovering flight

KW - Micro air vehicle

KW - Particle Image Velocimetry

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DO - 10.1007/978-81-322-2743-4_135

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JF - Lecture Notes in Mechanical Engineering

ER -

Particle image velocimetry measurements of rigid and flexible rectangular wings undergoing main flapping motion in hovering flight

Abstract

Bibliographical note

Keywords

ASJC Scopus subject areas

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