Experimental Analysis of a Small-Scale Rotor at Various Inflow Angles
The performance characteristics of a rotor that is typically used for small unmanned aircraft were analyzed in a series of wind-tunnel experiments. Wind-tunnel measurements were conducted with the rotor at various inflow angles in order to investigate the effects on the rotor performance of partiall...
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| Format: | Article |
| Language: | English |
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Wiley
2018-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2018/2560370 |
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| _version_ | 1841524843638423552 |
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| author | Amir Kolaei Devin Barcelos Götz Bramesfeld |
| author_facet | Amir Kolaei Devin Barcelos Götz Bramesfeld |
| author_sort | Amir Kolaei |
| collection | DOAJ |
| description | The performance characteristics of a rotor that is typically used for small unmanned aircraft were analyzed in a series of wind-tunnel experiments. Wind-tunnel measurements were conducted with the rotor at various inflow angles in order to investigate the effects on the rotor performance of partially or fully edgewise flow as they are typically encountered with small multirotor vehicles. Rotor tests were also performed under static and fully axial flow conditions in order to investigate the aerodynamic performance during hover as well as vertical climb and descent. The wind-tunnel data were corrected to account for the interference of wind-tunnel walls with the rotor wake and the blockage due to the presence of the rotor test stand in the wind-tunnel test section. The results are presented in terms of thrust, power, and roll moment coefficients under different rotor rotational speeds for a T-motor 18x6.1. Additionally, the measured thrust and power coefficients of Master Airscrew Electric 11x7 are compared with available propeller data under static and axial flow conditions for verification purposes. It is shown that the rotor performance characteristics are strongly affected by the freestream advance ratio and the freestream inflow angles. For example, at inflow angles that are typical for multirotor vehicles between about 15° and 0° with respect to the rotor disc, thrust coefficients stay constant or grow with increasing advance ratio, whereas power coefficients remain relatively constant with changing advance ratio. |
| format | Article |
| id | doaj-art-395b2b063e234a29a52a5e62f66bbda1 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2018-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-395b2b063e234a29a52a5e62f66bbda12025-02-03T05:47:15ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742018-01-01201810.1155/2018/25603702560370Experimental Analysis of a Small-Scale Rotor at Various Inflow AnglesAmir Kolaei0Devin Barcelos1Götz Bramesfeld2Ryerson Applied Aerodynamics Laboratory of Flight (RAALF), Department of Aerospace Engineering, Ryerson University, Toronto, Ontario, CanadaRyerson Applied Aerodynamics Laboratory of Flight (RAALF), Department of Aerospace Engineering, Ryerson University, Toronto, Ontario, CanadaRyerson Applied Aerodynamics Laboratory of Flight (RAALF), Department of Aerospace Engineering, Ryerson University, Toronto, Ontario, CanadaThe performance characteristics of a rotor that is typically used for small unmanned aircraft were analyzed in a series of wind-tunnel experiments. Wind-tunnel measurements were conducted with the rotor at various inflow angles in order to investigate the effects on the rotor performance of partially or fully edgewise flow as they are typically encountered with small multirotor vehicles. Rotor tests were also performed under static and fully axial flow conditions in order to investigate the aerodynamic performance during hover as well as vertical climb and descent. The wind-tunnel data were corrected to account for the interference of wind-tunnel walls with the rotor wake and the blockage due to the presence of the rotor test stand in the wind-tunnel test section. The results are presented in terms of thrust, power, and roll moment coefficients under different rotor rotational speeds for a T-motor 18x6.1. Additionally, the measured thrust and power coefficients of Master Airscrew Electric 11x7 are compared with available propeller data under static and axial flow conditions for verification purposes. It is shown that the rotor performance characteristics are strongly affected by the freestream advance ratio and the freestream inflow angles. For example, at inflow angles that are typical for multirotor vehicles between about 15° and 0° with respect to the rotor disc, thrust coefficients stay constant or grow with increasing advance ratio, whereas power coefficients remain relatively constant with changing advance ratio.http://dx.doi.org/10.1155/2018/2560370 |
| spellingShingle | Amir Kolaei Devin Barcelos Götz Bramesfeld Experimental Analysis of a Small-Scale Rotor at Various Inflow Angles International Journal of Aerospace Engineering |
| title | Experimental Analysis of a Small-Scale Rotor at Various Inflow Angles |
| title_full | Experimental Analysis of a Small-Scale Rotor at Various Inflow Angles |
| title_fullStr | Experimental Analysis of a Small-Scale Rotor at Various Inflow Angles |
| title_full_unstemmed | Experimental Analysis of a Small-Scale Rotor at Various Inflow Angles |
| title_short | Experimental Analysis of a Small-Scale Rotor at Various Inflow Angles |
| title_sort | experimental analysis of a small scale rotor at various inflow angles |
| url | http://dx.doi.org/10.1155/2018/2560370 |
| work_keys_str_mv | AT amirkolaei experimentalanalysisofasmallscalerotoratvariousinflowangles AT devinbarcelos experimentalanalysisofasmallscalerotoratvariousinflowangles AT gotzbramesfeld experimentalanalysisofasmallscalerotoratvariousinflowangles |