MATEC Web Conf.
Volume 234, 2018BulTrans-2018 – 10th International Scientific Conference on Aeronautics, Automotive and Railway Engineering and Technologies
|Number of page(s)||5|
|Published online||21 November 2018|
Experimental study of a helicopter rotor model in hover
1 Technical University of Sofia, Department of Air Transport, 8 Kliment Ohridski Blvd., 1000 Sofia, Bulgaria
2 Arts et Métiers – ParisTech, DynFluid laboratory, blvd. L’Hôpital 151, 75013 Paris, France
* Michael Todorov: Michael.Todorov@tu-sofia.bg
This paper presents the results from an experimental study of the aerodynamic performance and efficiency of a model helicopter rotor in steady hover at Reynolds numbers below 70000. Results are shown for a two-, three- and four-bladed rotor configuration for various pitch angles and speeds of rotation. The influence of the rotor solidity on the aerodynamic efficiency in terms of the Figure of Merit is highlighted. The profile drag component is evaluated as a function of the Reynolds number. The internal friction losses of the test stand are estimated and taken into account in all measurements. A brief description of the designed test stand is provided. The experimental setup allows for the measurement of thrust and torque of helicopter rotors with diameters of up to 1 meter, for pitch angles varying from -12° to +24° and for rotational speeds of up to 3000 RPM. Conclusions are drawn about the aerodynamic performance and efficiency of the studied rotor configurations. This experimental study provided a significant database, which will serve for validation purposes.
© The Authors, published by EDP Sciences, 2018
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 4.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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