Wing Flexibility Effects in Clap-and-Fling

Date

2011-12-01

Author

Perçin, Mustafa
van Oudheusden, B. W.
Remes, B.
Scarano, F.

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

125
views

0
downloads

The work explores the use of time-resolved tomographic PIV measurements to study a flapping-wing model, the related vortex generation mechanisms and the effect of wing flexibility on the clap-and-fling movement in particular. An experimental setup is designed and realized in a water tank by use of a single wing model and a mirror plate to simulate the wing interaction that is involved in clap-and-fling motion. The wing model used in the experiments has the same planform with the DelFly II wings and consists of a rigid leading edge and an isotropic polyester film. The thickness of the polyester film was changed in order to investigate the influence of flexibility. A similarity analysis based on the two-dimensional dynamic beam equation was performed to compare aeroelastic characteristics of flapping-wing motion in-air and in-water conditions. Based on the experimental results, the evolution of vortical structures during the clap-and-peel motion is explained. The general effects of flexibility on vortex formations and interactions are discussed. It was observed that the flexibility affects the behavior and orientation of the vortices in relation to the deformation of the wing and interaction with the mirror plate.

Subject Keywords

Hovering insect flight, Aerodynamics, Lift, Mechanisms

URI

https://hdl.handle.net/11511/34503

Journal

INTERNATIONAL JOURNAL OF MICRO AIR VEHICLES

DOI

https://doi.org/10.1260/1756-8293.3.4.217

Collections

Department of Aerospace Engineering, Article

Suggestions

OpenMETU
Core

Wing flutter analysis with an uncoupled method Kavukcuoğlu, Koray; Akgün, Mehmet A.; Oktay, Erdal; Department of Aerospace Engineering (2003) In this thesis, flutter of AGARD Wing 445.6 is predicted with a new approach. The unsteady aerodynamic loads are calculated with an unstructured Euler solver. Surface interpolation is used to transfer the calculated mode shapes from the structural mesh to the CFD mesh and to transfer pressure distributions in the opposite direction. Using the transferred pressure distributions, nodal force distributions on the finite element model are calculated. A polynomial is fitted to the nodal forces in terms of the re...
Three-dimensional vortex wake structure of a flapping-wing micro aerial vehicle in forward flight configuration Perçin, Mustafa; Eisma, H. E.; Remes, B. D. W. (2014-09-01) This paper investigates the formation and evolution of the unsteady three-dimensional wake structures generated by the flapping wings of the DelFly II micro aerial vehicle in forward flight configuration. Time-resolved stereoscopic particle image velocimetry (Stereo-PIV) measurements were carried out at several spanwise-aligned planes in the wake, so as to allow a reconstruction of the temporal development of the wake of the flapping wings throughout the complete flapping cycle. Simultaneous thrust-force me...
Aeroelastic Analysis of a Flapping Blow Fly Wing Beker, Can; Turgut, Ali Emre; ARIKAN, KUTLUK BİLGE; Kurtuluş, Dilek Funda (2020-06-01) In this study, a 3D model of the bio-inspired blowfly wing Callphere Erytrocephala is created and aeroelastic analysis is performed to calculate its aerodynamical characteristics by use of numerical methods. To perform the flapping motion, a sinusoidal input function is created. The scope of this study is to perform aeroelastic analysis by synchronizing computational fluid dynamics (CFD) and structural dynamic analysis models and to investigate the unsteady lift formation on the aeroelastic flapping wing fo...
Control and Robustness Analysis for a High-alpha Maneuverable Thrust-Vectoring Fighter Aircraft Atesoglu, Oezguer; Özgören, Mustafa Kemal (2009-09-01) This study focuses on designing a nonlinear controller for high-alpha maneuvers of a fighter aircraft with a thrust-vectoring control ability and checking the robustness of the designed controller using the structured singular-value mu-based robustness analysis. The controller is designed using the nonlinear dynamic inversion method. It is designed, to engage either the aerodynamic control surfaces or the thrust-vectoring control paddles of the engines, depending on the flight conditions. The necessary math...
Flow field characteristics of translating and revolving flexible wings Yazdanpanah, Mahdi; Hazaveh, Hooman Amiri; Perçin, Mustafa; Van De Meerendonk, Remco; Van Oudheusden, Bas W. (null; 2019-10-20) This study explores the effects of rotational mechanisms on the characteristics of the leading edge vortex (LEV) by comparing translating and revolving flexible wings that are started from rest. Tomographic particle image velocimetry (tomographic-PIV) technique was employed to acquire three-dimensional flow fields for the revolving wings, while planar flow fields for the case of translating wings were acquired via 2D2C-PIV measurements. The comparison of flow fields between the two motion kinematics reveal...

Citation Formats

M. Perçin, B. W. van Oudheusden, B. Remes, and F. Scarano, “Wing Flexibility Effects in Clap-and-Fling,” INTERNATIONAL JOURNAL OF MICRO AIR VEHICLES, pp. 217–227, 2011, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/34503.