Next Article in Journal / Special Issue
Hydrodynamic Performance of Aquatic Flapping: Efficiency of Underwater Flight in the Manta
Previous Article in Journal
Large Scale Applications Using FBG Sensors: Determination of In-Flight Loads and Shape of a Composite Aircraft Wing
Previous Article in Special Issue
The Effect of the Phase Angle between the Forewing and Hindwing on the Aerodynamic Performance of a Dragonfly-Type Ornithopter
Article Menu

Export Article

Open AccessArticle
Aerospace 2016, 3(3), 19; doi:10.3390/aerospace3030019

The Efficiency of a Hybrid Flapping Wing Structure—A Theoretical Model Experimentally Verified

Faculty of Aerospace Engineering, Technion, Israel Institute of Technology, 32000 Haifa, Israel
*
Author to whom correspondence should be addressed.
Academic Editor: Sutthiphong Srigrarom
Received: 7 April 2016 / Revised: 22 June 2016 / Accepted: 30 June 2016 / Published: 5 July 2016
(This article belongs to the Special Issue Flapping Wings)

Abstract

To propel a lightweight structure, a hybrid wing structure was designed; the wing’s geometry resembled a rotor blade, and its flexibility resembled an insect’s flapping wing. The wing was designed to be flexible in twist and spanwise rigid, thus maintaining the aeroelastic advantages of a flexible wing. The use of a relatively “thick” airfoil enabled the achievement of higher strength to weight ratio by increasing the wing’s moment of inertia. The optimal design was based on a simplified quasi-steady inviscid mathematical model that approximately resembles the aerodynamic and inertial behavior of the flapping wing. A flapping mechanism that imitates the insects’ flapping pattern was designed and manufactured, and a set of experiments for various parameters was performed. The simplified analytical model was updated according to the tests results, compensating for the viscid increase of drag and decrease of lift, that were neglected in the simplified calculations. The propelling efficiency of the hovering wing at various design parameters was calculated using the updated model. It was further validated by testing a smaller wing flapping at a higher frequency. Good and consistent test results were obtained in line with the updated model, yielding a simple, yet accurate tool, for flapping wings design. View Full-Text
Keywords: flapping wing; Reynolds number; hovering wing; micro air vehicles (MAV); airfoil; tests; figure of merit; rotating blade flapping wing; Reynolds number; hovering wing; micro air vehicles (MAV); airfoil; tests; figure of merit; rotating blade
Figures

This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. (CC BY 4.0).

Scifeed alert for new publications

Never miss any articles matching your research from any publisher
  • Get alerts for new papers matching your research
  • Find out the new papers from selected authors
  • Updated daily for 49'000+ journals and 6000+ publishers
  • Define your Scifeed now

SciFeed Share & Cite This Article

MDPI and ACS Style

Keren, Y.; Abramovich, H.; Arieli, R. The Efficiency of a Hybrid Flapping Wing Structure—A Theoretical Model Experimentally Verified. Aerospace 2016, 3, 19.

Show more citation formats Show less citations formats

Note that from the first issue of 2016, MDPI journals use article numbers instead of page numbers. See further details here.

Related Articles

Article Metrics

Article Access Statistics

1

Comments

[Return to top]
Aerospace EISSN 2226-4310 Published by MDPI AG, Basel, Switzerland RSS E-Mail Table of Contents Alert
Back to Top