Experimental Investigation of the Aerodynamic Characteristics of Flapping-Wing Micro Air Vehicles
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Authors
Jones, K.D.
Platzer, M.F.
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Date of Issue
2003
Date
2003
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Abstract
In this paper the development and flight testing of a radio-controlled micro air vehicle propelled by flapping wings is described. The vehicle consists of a 30cm-span, 14.5cm-chord fixed-wing, with two flapping wings immediately downstream of the fixed-wing. The flapping wings, with a 25cm-span and 4cm-chord, are arranged in a biplane configuration and flap in counterphase, providing a mechanically and aerodynamically balanced platform. Flight tests have shown that the configuration is particularly well suited for low speed flight, due to the inherent resistance to flow separation facilitated by flow entrainment from the flapping wing pair. The 14 gram model has demonstrated stable flight at speeds between 2 and 5m/s, and the model exhibits a very rapid stall recovery under power, due to the flow entrainment effect.
Type
Conference Paper
Description
AIAA Paper No. 2003-0418, Reno, Nevada, Jan. 2003.
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Department
Department of Mechanical and Aerospace Engineering
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Citation
Jones, K.D. and Platzer, M.F., "Experimental Invesitigation of the Aerodynamic Characteristics of Flapping-Wing Micro Air Vehicles," AIAA Paper No. 2003-0418, Reno, Nevada, Jan. 2003.
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This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.