Hostname: page-component-8448b6f56d-mp689 Total loading time: 0 Render date: 2024-04-19T10:54:57.246Z Has data issue: false hasContentIssue false
  • English
  • Français

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
Get access Rights & Permissions [Opens in a new window]

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 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Newman, S.J. A theoretical model for predicting the blade sailing behaviour of a semi rigid rotor helicopter, Vertica, 1990, 14, (4), pp 531–544.Google Scholar
2. Newman, S.J. The application of a theoretical blade sailing model to predict the behaviour of articulated helicopter rotors. Aeronaut J, June/July 1992, 96, (956), pp 233–239.Google Scholar
3. Hurst, D.W. and Newman, S.J. Windtunnel measurements of ship induced turbulence and the prediction of helicopter rotor blade response, Vertica, 1988,12, (3), pp 267–278.Google Scholar
4.Westland Lynx/Ship Interface, Brochure B1163 Issue 2, Westland Helicopters Ltd, Yeovil, Somerset, June 1985.Google Scholar
5. Newman, S.J. A windtunnel investigation into the blade sailing be haviour of a model teetering rotor operating from the simulated flight deck of a Rover class Royal Fleet Auxiliary vessel. AASU 91/2, Department of Aeronautics and Astronautics, University of Southampton, September 1991.Google Scholar
6. Beddoes, T.S. An analytical model for trailing edge stall, RP 637, Westland Helicopters Ltd, April 1981.Google Scholar
7. Press, W.H., Flannery, B.P., Teukolsky, S.A. and Vetterling, W.T. Numerical Recipes — The art of scientific computing, Cambridge University Press 1986.Google Scholar
8. Piercy, N.A.V. Aerodynamics, The English Universities Press, 1937.Google Scholar