Experimental study of a helicopter rotor model in hover
| Autor: | Fawaz Massouh, Michael Todorov, Filip Panayotov, Ivan Dobrev |
|---|---|
| Rok vydání: | 2018 |
| Předmět: |
business.industry
Rotor (electric) Reynolds number Thrust 02 engineering and technology Aerodynamics Structural engineering Rotation 01 natural sciences 010305 fluids & plasmas law.invention symbols.namesake 020303 mechanical engineering & transports 0203 mechanical engineering lcsh:TA1-2040 law Parasitic drag 0103 physical sciences symbols Solidity Helicopter rotor lcsh:Engineering (General). Civil engineering (General) business |
| Zdroj: | MATEC Web of Conferences, Vol 234, p 01002 (2018) |
| ISSN: | 2261-236X |
| Popis: | 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. |
| Databáze: | OpenAIRE |
| Externí odkaz: |
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