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The verification of a theoretical helicopter rotor blade sailing method by means of windtunnel testing

Published online by Cambridge University Press:  04 July 2016

S. J. Newman
S. J. Newman*
Affiliation:
Department of Aeronautics and Astronautics, University of Southampton
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Extract

The performance of a helicopter rotor has always been dogged by the dissymmetry of air velocity over the blades caused by its translation in a direction substantially parallel to the plane of the rotor disc. Furthermore, in order to make the rotor even usable, this dissymmetry of lift has caused the introduction of major mechanical complications to the rotor hub. In forward flight the rotor is aerodynamically split into two halves either side of the flight direction. The advancing side, where the rotor rotation is in the same sense as the forward velocity, will see a greater dynamic head than the retreating side, where the rotor rotation and forward speed are in opposition. A rigid rotor would consequently suffer a major rolling moment and if a viable proposition is to be achieved the rolling moment must be avoided.

Type
Research Article
Information
The Aeronautical Journal , Volume 99 , Issue 982 , February 1995 , pp. 41 - 51
Copyright
Copyright © Royal Aeronautical Society 1995 

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References

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