The aerodynamics phenomena of flapping motion in hover are considered in view of
the future Micro Air Vehicle applications. The aim of this work is to characterize the
vortex dynamics generated by the wing in motion using direct numerical simulation
and experimental analysis then to propose a simplified analytical model for
prediction of the forces in order to optimize the parameters of the motion leading to
maximum force. A great number of cases are investigated corresponding to different
angles of attack, location of start of change of incidence, location of start of change
of velocity, axis of rotation, and Re number. The airfoil used is symmetrical. The
flow is assumed to be incompressible and laminar with the Reynolds numbers
between 500 and 2000. The experimental results obtained by the laser sheet
visualization and the Particle Image Velocimetry (PIV) techniques are used in
parallel with the direct numerical simulation results for the phenomenological
analysis of the flow. The model developed for the aerodynamic forces is an indicial method based on the use of the Duhamel Integral and the results obtained by this
model are compared with the ones of the numerical simulations.
| Identifer | oai:union.ndltd.org:METU/oai:etd.lib.metu.edu.tr:http://etd.lib.metu.edu.tr/upload/12606168/index.pdf |
| Date | 01 June 2005 |
| Creators | Kurtulus, Dilek Funda |
| Contributors | Alemdaroglu, Nafiz |
| Publisher | METU |
| Source Sets | Middle East Technical Univ. |
| Language | English |
| Detected Language | English |
| Type | Ph.D. Thesis |
| Format | text/pdf |
| Rights | To liberate the content for public access |
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