STUDY OF FLAPPING FLIGHT USING DISCRETE VORTEX METHOD BASED SIMULATIONS

S. Devranjan, Shreyas V. Jalikop and K. R. Sreenivas ()
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S. Devranjan: Jawaharlal Nehru Centre for Advanced Scientific Research, Bangalore-560 064, India
Shreyas V. Jalikop: Jawaharlal Nehru Centre for Advanced Scientific Research, Bangalore-560 064, India
K. R. Sreenivas: Jawaharlal Nehru Centre for Advanced Scientific Research, Bangalore-560 064, India

International Journal of Modern Physics C (IJMPC), 2013, vol. 24, issue 12, 1-8

Abstract: In recent times, research in the area of flapping flight has attracted renewed interest with an endeavor to use this mechanism in Micro Air vehicles (MAVs). For a sustained and high-endurance flight, having larger payload carrying capacity we need to identify a simple and efficient flapping-kinematics. In this paper, we have used flow visualizations and Discrete Vortex Method (DVM) based simulations for the study of flapping flight. Our results highlight that simple flapping kinematics with down-stroke period(tD)shorter than the upstroke period(tU)would produce a sustained lift. We have identified optimal asymmetry ratio(Ar = tD/tU), for which flapping-wings will produce maximum lift and find that introducing optimal wing flexibility will further enhances the lift.

Keywords: Flapping flight; asymmetric-flapping; MAV; wing-flexibility; 47.85.Gj; 47.40.-x; 47.20.-k; 47.11.-j; 47.63.-b (search for similar items in EconPapers)
Date: 2013
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DOI: 10.1142/S012918311340007X

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