### Abstract

High-speed videography is used in measuring the kinematic and deformation parameters of the flapping wing. Based on these data, a theoretical analysis of the underlying physics is performed using computational fluid dynamics simulations. The time varying of the pitching angle in the chordwise directions exhibits a significant second harmonic. Results suggest the mechanics of membrane deformations during a flapping cycle is analogous to the buckling of a bistable structure. Noticeably, with an increase in the freestreamspeed, the downstroke duration increases. The solution to the three-dimensional fluid dynamics problem is constructed using two-dimensional solutions obtained for several sections of the wing by the improved discrete vortex method. The inertial component is dominant in the normal force coefficient, and hence, added mass is the main mechanism in aerodynamic force production for the studied problem. A normal component of the acceleration of the wing's trailing edge taken with a negative sign is introduced as a kinematic parameter that is essential in flapping-wing aerodynamics. The results show a satisfactory agreement in trends of the acceleration and force coefficients. From the analysis of kinematical changes, it follows that synchronization of acceleration and of the pitching angle is important for achieving maximum values of the vertical force coefficients.

Original language | English (US) |
---|---|

Pages (from-to) | 1734-1747 |

Number of pages | 14 |

Journal | Journal of Aircraft |

Volume | 50 |

Issue number | 6 |

DOIs | |

State | Published - Nov 2013 |

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### ASJC Scopus subject areas

- Aerospace Engineering

### Cite this

*Journal of Aircraft*,

*50*(6), 1734-1747. https://doi.org/10.2514/1.C032053

**Experimental and computational modeling of the kinematics and aerodynamics of flapping wing.** / Shkarayev, Sergey V; Maniar, Gunjan; Shekhovtsov, Alexander V.

Research output: Contribution to journal › Article

*Journal of Aircraft*, vol. 50, no. 6, pp. 1734-1747. https://doi.org/10.2514/1.C032053

}

TY - JOUR

T1 - Experimental and computational modeling of the kinematics and aerodynamics of flapping wing

AU - Shkarayev, Sergey V

AU - Maniar, Gunjan

AU - Shekhovtsov, Alexander V.

PY - 2013/11

Y1 - 2013/11

N2 - High-speed videography is used in measuring the kinematic and deformation parameters of the flapping wing. Based on these data, a theoretical analysis of the underlying physics is performed using computational fluid dynamics simulations. The time varying of the pitching angle in the chordwise directions exhibits a significant second harmonic. Results suggest the mechanics of membrane deformations during a flapping cycle is analogous to the buckling of a bistable structure. Noticeably, with an increase in the freestreamspeed, the downstroke duration increases. The solution to the three-dimensional fluid dynamics problem is constructed using two-dimensional solutions obtained for several sections of the wing by the improved discrete vortex method. The inertial component is dominant in the normal force coefficient, and hence, added mass is the main mechanism in aerodynamic force production for the studied problem. A normal component of the acceleration of the wing's trailing edge taken with a negative sign is introduced as a kinematic parameter that is essential in flapping-wing aerodynamics. The results show a satisfactory agreement in trends of the acceleration and force coefficients. From the analysis of kinematical changes, it follows that synchronization of acceleration and of the pitching angle is important for achieving maximum values of the vertical force coefficients.

AB - High-speed videography is used in measuring the kinematic and deformation parameters of the flapping wing. Based on these data, a theoretical analysis of the underlying physics is performed using computational fluid dynamics simulations. The time varying of the pitching angle in the chordwise directions exhibits a significant second harmonic. Results suggest the mechanics of membrane deformations during a flapping cycle is analogous to the buckling of a bistable structure. Noticeably, with an increase in the freestreamspeed, the downstroke duration increases. The solution to the three-dimensional fluid dynamics problem is constructed using two-dimensional solutions obtained for several sections of the wing by the improved discrete vortex method. The inertial component is dominant in the normal force coefficient, and hence, added mass is the main mechanism in aerodynamic force production for the studied problem. A normal component of the acceleration of the wing's trailing edge taken with a negative sign is introduced as a kinematic parameter that is essential in flapping-wing aerodynamics. The results show a satisfactory agreement in trends of the acceleration and force coefficients. From the analysis of kinematical changes, it follows that synchronization of acceleration and of the pitching angle is important for achieving maximum values of the vertical force coefficients.

UR - http://www.scopus.com/inward/record.url?scp=84892591851&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84892591851&partnerID=8YFLogxK

U2 - 10.2514/1.C032053

DO - 10.2514/1.C032053

M3 - Article

AN - SCOPUS:84892591851

VL - 50

SP - 1734

EP - 1747

JO - Journal of Aircraft

JF - Journal of Aircraft

SN - 0021-8669

IS - 6

ER -