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 |
| _version_ | 1811694173562077184 |
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| author | Wee, Raun Joshua Guanwei. |
| author2 | School of Mechanical and Aerospace Engineering |
| author_facet | School of Mechanical and Aerospace Engineering Wee, Raun Joshua Guanwei. |
| author_sort | Wee, Raun Joshua Guanwei. |
| collection | NTU |
| description | 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. |
| first_indexed | 2024-10-01T07:03:22Z |
| format | Final Year Project (FYP) |
| id | ntu-10356/50167 |
| institution | Nanyang Technological University |
| language | English |
| last_indexed | 2024-10-01T07:03:22Z |
| publishDate | 2012 |
| record_format | dspace |
| spelling | ntu-10356/501672023-03-04T19:00:31Z Solar UAV: aerodynamic design and model testing in a wind tunnel Wee, Raun Joshua Guanwei. School of Mechanical and Aerospace Engineering Simon Yu Tonse Gokuldas Pai DRNTU::Engineering 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. Bachelor of Engineering (Aerospace Engineering) 2012-05-30T07:26:37Z 2012-05-30T07:26:37Z 2012 2012 Final Year Project (FYP) http://hdl.handle.net/10356/50167 en Nanyang Technological University 172 p. application/pdf |
| spellingShingle | DRNTU::Engineering Wee, Raun Joshua Guanwei. Solar UAV: aerodynamic design and model testing in a wind tunnel |
| title | Solar UAV: aerodynamic design and model testing in a wind tunnel |
| title_full | Solar UAV: aerodynamic design and model testing in a wind tunnel |
| title_fullStr | Solar UAV: aerodynamic design and model testing in a wind tunnel |
| title_full_unstemmed | Solar UAV: aerodynamic design and model testing in a wind tunnel |
| title_short | Solar UAV: aerodynamic design and model testing in a wind tunnel |
| title_sort | solar uav aerodynamic design and model testing in a wind tunnel |
| topic | DRNTU::Engineering |
| url | http://hdl.handle.net/10356/50167 |
| work_keys_str_mv | AT weeraunjoshuaguanwei solaruavaerodynamicdesignandmodeltestinginawindtunnel |