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Case Study on Investigation of Aerofoil for Flapping Wing Aircraft


Case Study on Investigation of Aerofoil for Flapping Wing Aircraft
Authors : Karrothu V R Manikanta, N. Muralikrishna, N.Sathish, G. Sampath Kumar
Publication Date: 05-08-2015

Authors

Author(s):  Karrothu V R Manikanta, N. Muralikrishna, N.Sathish, G. Sampath Kumar

Published in:   International Journal of Engineering Research & Technology

License:  This work is licensed under a Creative Commons Attribution 4.0 International License.

Website: www.ijert.org

Volume/Issue:   Volume. 4 - Issue. 08 , August - 2015

e-ISSN:   2278-0181

 DOI:  http://dx.doi.org/10.17577/IJERTV4IS080094

Abstract

Flapping-wing aerodynamics recently has generated a great deal of interest and increasing research effort because of the potential application in micro-air vehicles and mainly in military applications. The aim of this project is to optimize the better and efficient aerofoil in wing design of eagle-sized flapping wing aircraft and also capable of hovering flight. Depends on viability of Ornithopters, three different characteristic aerofoils were selected. The analysis of aerofoil is carried out by using Computational Fluid Dynamics (CFD). Computations have been made adopting structural grid and k-ω turbulence model using commercial software Fluent. The results are consists of flow visualization graphs, aerodynamic drag and lift values. CFD can be used to simulate the flow over any object. We believe that the results showed in this paper will be useful for future research in development of design of flapping wing aircraft.

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