The effects of the wing motion on the aerodynamics of a MAV

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The effects of the wing motion on the aerodynamics of a MAV

 

Author: Shi, Lisong
Title: The effects of the wing motion on the aerodynamics of a MAV
Degree: M.Sc.
Year: 2014
Subject: Airplanes -- Wings.
Micro air vehicles.
Hong Kong Polytechnic University -- Dissertations
Department: Faculty of Engineering
Pages: ix, 75 leaves : ill. (some col.) ; 30 cm.
Language: English
InnoPac Record: http://library.polyu.edu.hk/record=b2747497
URI: http://theses.lib.polyu.edu.hk/handle/200/7441
Abstract: This is an experimental study of aerodynamic performance of micro air vehicle (MAV), consists of four parts: (1) Particle Image Velocimetry Programming - Particle Image Velocimetry (PIV) is employed for instantaneous flow visualization; it is a complex system which can be influenced by multiple parameters; aside from the coordination among the equipment, different methodologies used in post-processing of the PIV image have distinct characteristic in both accuracy and efficiency; MATLAB codes for PIV is evaluated based on both Direct Discrete Correlation and Fast Fourier Transform methods, comparison between the two algorithms is analyzed. (2) Aerodynamics of a single flapping wing - Under zero free stream condition, complex instantaneous vortex topology is investigated for a flapping wing at half of the wing length, the cause-and-effect between vortex shedding and lift generation is analyzed; furthermore, vortex topology with flapping frequencies of 8Hz and 12Hz is studied qualitatively for its impact on instantaneous lift. (3) The process of Clap-Fling motion - As an important and also complicated feature of insects flying, Clap-Fling motion is engaged in the design of current MAV. Experiment is conducted at 10Hz with zero free stream, the vortices distributions surrounding the Clap-Fling mechanism developed from the averaged PIV data at successive moments of one cycle unveil a number of important aspects of the Clap-Fling. (4) The wake behind MAV - For the MAV in this research, the corresponding angle of attack with certain flow velocity is carefully selected based on the horizontal component of the time-averaged force equals to zero, which indicates the ideal situation for level flying. With the appropriate condition for level flying, the evolution of the flow structure in the downstream of the MAV is analyzed in correlation with the lift measurement, to release the concealed physics for MAV.

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