Solar UAV: aerodynamic design and model testing in a wind tunnel
The baseline configuration of a solar-powered unmanned aerial vehicle (UAV) with an endurance of 24 hours at a cruise altitude of 8000m is determined through market research, analysis of the mission requirements and aerodynamic considerations. Using the baseline configuration, a 1:27 scale...
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| Format: | Final Year Project (FYP) |
| Language: | English |
| Published: |
2012
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| Online Access: | http://hdl.handle.net/10356/50167 |
| Summary: | The baseline configuration of a solar-powered unmanned aerial vehicle (UAV) with an
endurance of 24 hours at a cruise altitude of 8000m is determined through market research,
analysis of the mission requirements and aerodynamic considerations. Using the baseline
configuration, a 1:27 scale model was designed and built meeting the low speed test
requirements on side wall effects and model blockage. The scale model was tested using the
available 6 component balance in the closed circuit wind tunnel at Nanyang Technological
University over a range of model configurations including wings with and without dihedral
and control deflections. Analysis of the balance measurements were carried out to obtain
longitudinal characteristics – lift, drag and pitching moment, of the Solar UAV. Both the
straight wing and dihedral wing configurations were found to have acceptable lifting and
pitching moment characteristics. However the drag data measured in the present tests on
the 1:27 scale model using the available balance is found to be unacceptable due to the
smaller test Reynolds number compared to the flight Reynolds number and the large full
scale load ranges of the force balance used. |
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