Experiments on Rigid Wing Undergoing Hover-Capable Flapping Kinematics at Micro-Air-Vehicle-Scale Reynolds Numbers

Benedict, Moble; Coleman, David; Mayo, David B.; Chopra, Inderjit

doi:10.2514/1.j052947

Cited by 8 publications

(8 citation statements)

References 19 publications

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“…The measured force curve is not well tracked in its relaxation toward state-state conditions. • Ω dn Single-plane drift-volume contribution, Ahsan and Aureli (2017)), the dynamics of natural swimmers and flyers (Bos et al (2008) and Eloy (2013)), as well as to provide a design basis for engineering development; for example, modern interests include micro aerial vehicles (Ansari et al (2006) and Benedict et al (2016)). The ability to measure instantaneous dynamic loading gives physical insight into the fluid mechanics responsible for force generation.…”

Section: 3mentioning

confidence: 99%

Unsteady force estimation using a Lagrangian drift-volume approach

McPhaden

Rival

2018

Exp Fluids

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A novel Lagrangian force estimation technique for unsteady fluid flows has been developed, using the concept of a Darwinian drift volume to measure the unsteady force on an accelerating body. A methodology using multiple drift volumes is described and evaluated on an experimental test case containing highly-separated, vortical flow. The inherent advantage of the force estimation technique presented is that, unlike many modern Eulerian techniques, gradient operations and near-body measurements are not required to be calculated. These noise amplifying processes are avoided since the drift volume is calculated only from particle displacements in the flow field, reducing the importance of having high quality acceleration and spatial gradient data near walls and in regions of high shear. The resultant unsteady force estimates from the proposed technique are shown to align with the measured drag force during high accelerations, a region in which comparable methods suffer. The critical aspects of understanding unsteady flows, relating to peak and time-resolved forces, often lie within the acceleration phase of the motions, which are well-captured by the drift-volume approach. Therefore, this Lagrangian force estimation technique opens the door to fluid-dynamic analyses in areas that, until now, were inaccessible by conventional means. i Above all else, I would like to thank my supervisor, Dr. David Rival, for his knowledge and teaching, for affording me the opportunities to learn and collaborate with the world's best, for his patience and understanding, and for making me learn the hard way that nothing is ever perfect. I would like to thank all my research group colleagues, specifically Drs. John Fernando, Giuseppe Rosi and Amirreza Rouhi, for their guidance and constructive conversations over the past years. Special thanks goes out to Dr. Jaime Wong for his assistance and dedication of time toward my research. I must also acknowledge the financial support from the Ontario Graduate Scholarship and the Natural Sciences and Engineering Research Council of Canada, which made this work possible. I would like extend a sincere thank you to the entire First Capital Cycling community for taking me in as one of their own. In particular, I owe a large debt of gratitude to Ka-Yu, Matt, Andy, Jim and Sue for being quality role models, pushing my limits, and challenging me to always become a better version of myself. To my family: Thank you for your unwavering support in all aspects of my life over the course of the last few years. Without you all, I would not have made it to where I am today.

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Section: 3mentioning

confidence: 99%

Unsteady force estimation using a Lagrangian drift-volume approach

McPhaden

Rival

2018

Exp Fluids

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“…The estimated uncertainty of the measured velocity within the experimental flowfield measurements is 0.667%. A more detailed description of the experimental set-up and procedure can be found in Benedict et al 26…”

Section: Computational Methodology and Validation Experiments Descriptmentioning

confidence: 99%

“…To validate the results from the numerical simulation, the force and flowfield data from the experiment conducted on a rigid, bio-inspired low AR wing by Benedict et al. 26 were utilized for comparison. The wing used throughout the experiment, depicted in Figure 1, consists of a stiff carbon fiber frame covered by a thin Mylar membrane film resulting in a total wing weight of 3 g. Wing length ( b ) and thickness ( h ) were 15.24 cm and 1.6 mm, respectively.…”

Section: Computational Methodology and Validation Experiments Descriptionmentioning

confidence: 99%

“…The power loading variation over the translational phase of the flap cycle for the forward stroke and backward stroke is shown in Figure 14. Figure 14(a) also contains experimental data for instantaneous liftto-power ratio presented in Benedict et al 26 Note that the available experimental data are only for the forward stroke from approximately t/T ¼ 0.2À0.4, which omits regions of negative lift in the lift-to-power ratio trends. Similar to Figure 13, there is little difference between the computational trends predicted in the forward stroke in comparison to the backward stroke.…”

Section: Aerodynamic Power and Efficiencymentioning

confidence: 99%

“…Recently, Benedict et al. 26 performed instantaneous force measurements and flowfield studies on a rigid wing undergoing active insect-like flapping kinematics with passive pitch rotations. Given that one of the main objectives of the study was to validate the applicability of an inertial force subtraction method in air, only a limited set of flowfield experiments were performed.…”

Section: Introductionmentioning

confidence: 99%

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Computational investigation of insect-based flapping wings for micro air vehicle applications

Mayo

Chopra

2016

International Journal of Micro Air Vehicles

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In this study, a computational fluid dynamics analysis was performed on bio-inspired micro aerial vehicle scale rigid flapping wings. The computational fluid dynamics analysis used a compressible unsteady Reynolds Averaged NavierStokes solver with low-Mach number preconditioning to study the complex, highly vortical, three-dimensional flow of low aspect ratio flapping wings at micro aerial vehicle-scale Reynolds numbers. The wing was flapped at a constant 5 Hz flap frequency at a mean chord reference Reynolds number of 25,000. The flapping and pitching kinematics were set to match those of a previous experimental study resulting in a constant flap stroke of 107 at translational pitching angles of 40 , 50 , and 60 . The force and flowfield measurements of the previous flapping-wing experiment were used for the validation of the 3D computational fluid dynamics model. The objectives of this effort were to understand the unsteady aerodynamic mechanisms and their relation to force production and aerodynamic efficiency on a rigid wing undergoing an insect-type flapping motion with passive pitching kinematics. Overall, the computational fluid dynamics results showed good agreement with the measured experimental force data. Additionally, the computational fluid dynamics simulation was able to adequately predict the process of leading edge vortex formation and shedding observed during experimentation. A vorticity summation approach used to calculate the strength of the leading edge vortex from the experimental measurements and from the computational fluid dynamics predicted flowfields showed comparable results. The computational fluid dynamics results were utilized to further analyze the differences in the flowfield and leading edge vortex formation for the three pitch angles tested as well as the instantaneous aerodynamic loads and aerodynamic power.

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Long-term two-dimensional analysis of the flow field around a hovering flapping flat-plate wing

Yamazaki

Okabe

2023

JFST

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Experiments on Rigid Wing Undergoing Hover-Capable Flapping Kinematics at Micro-Air-Vehicle-Scale Reynolds Numbers

Cited by 8 publications

References 19 publications

Unsteady force estimation using a Lagrangian drift-volume approach

Unsteady force estimation using a Lagrangian drift-volume approach

Computational investigation of insect-based flapping wings for micro air vehicle applications

Long-term two-dimensional analysis of the flow field around a hovering flapping flat-plate wing

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