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Advancement of aerofoil section dynamic stall synthesis methods for rotor design

Published online by Cambridge University Press:  27 January 2016

W. Sheng ,
W. Chan  and
R. Galbraith
W. Sheng
Affiliation:
Glasgow University, Glasgow, UK
W. Chan*
Affiliation:
Yeovil, UK
R. Galbraith
Affiliation:
Glasgow University, Glasgow, UK
*
[email protected]
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Abstract

Dynamic stall is a complex process encountered by an aerofoil in the unsteady flow environment such as a helicopter rotor in forward flight as well as a fixed wing aircraft in manoeuvres and in other unsteady situations. The onset of dynamic stall effectively determines the flight envelope of the helicopter. Significant effort are being made to develop CFD to capture the dynamic stall behaviour, however traditional engineering models based on lifting line theory still offer fast turn-round and broad understanding required for the rotor design process. This paper describes a new engineering model for dynamic stall, developed originally for wind turbine application at a typical Mach number of 0·12. The new dynamic stall model, with a better definition of stall onset, is based on improvements made to Beddoes’ original trailing edge stall model. This paper will describe and demonstrate the improvements in identifying both the stall-onset and the pitching moment break at high pitch rates, when being applied to a generic rotor aerofoil RAE 9651 at M = 0·3. Further validation against oscillatory tests and other Mach numbers are still required. However the study has provided sufficient confidence for it to be employed in a rotor analysis code.

Type
Research Article
Information
The Aeronautical Journal , Volume 116 , Issue 1179 , May 2012 , pp. 521 - 539
Copyright
Copyright © Royal Aeronautical Society 2012 

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References

1. Wilby, P.G. The aerodynamic characteristics of some new RAE blade sections, and their potential influence on rotor performance, Vertica, 1980, 4, pp 121–133.Google Scholar
2. Wilby, P.G. The development of rotor airfoil testing in the UK, J American Helicopter Society, July 2001, 46, pp 210–220.Google Scholar
3. Leishman, J.G. Principles of Helicopter Aerodynamics, p 529 (2nd ed), Cambridge Aerospace Series, Cambridge University Press, Cambridge, UK, 2006.Google Scholar
4. Beddoes, T.S. Representation of Airfoil Behavior, Vertica, 1983, 7, (2), p 183–197.Google Scholar
5. Leishman, J.G. and Beddoes, T.S. A Semi-Empirical model for dynamic stall, J American Helicopter Society, July 1989, 34, pp 3–17.Google Scholar
6. Sheng, W., Galbraith, R.A.McD. and Cotton, F.N. A Modified Dynamic Stall Model for Low Mach Numbers, submitted to J Solar Energy Engineering, and also presented at 45th AIAA Aerospace Sciences Meeting and Exhibit (AIAA 2007-0626), Reno, USA, January 2007.Google Scholar
7. Sheng, W., Galbraith, R.A.McD. and Coton, F.N. On the Return from Aerofoil Stall during Rampdown Pitching Motions, accepted by J Aircr, and also presented at 45th AIAA Aerospace Sciences Meeting and Exhibit (AIAA 2007-1075), Reno, USA, January 2007.Google Scholar
8. Mccroskey, W.J., McAlister, K.W., Carr, L.W., Pucci, S.L., Lambert, O. and Indergrand, R.F. dynamic stall on Advanced airfoil sections, J American Helicopter Society, 26 July 1981, pp 40–50.Google Scholar
9. Sheng, W., Galbraith, R.A.McD. and Coton, F.N. A new stall-onset criterion for low speed dynamic-stall, J Solar Energy Engineering, 2006, 128, pp 461–471.Google Scholar
10. Seto, L.Y. and Galbraith, R.A.McD. The Effect of Pitch Rate on the Dynamic Stall of a NACA23012 Aerofoil, presented at 11th European Rotorcraft Forum, London, UK, 1985.Google Scholar
11. Sheng, W., Galbraith, R.A.McD. and Coton, F.N. Improved stall-onset criterion for low Mach Numbers, J Aircr, 2007, 44, (3), pp 1049–1052.Google Scholar
12. Sheng, W., Galbraith, R.A.McD. and Coton, F.N. Prediction of Dynamic-Stall Onset for Oscillatory Low Speed Aerofoils, to be published.Google Scholar
13. Humphreys, C. Results of Oscillatory Pitch, Ramp and Drag Tests on the RAE 9651 Section, ARA model Test Note M161/2, 1&2, 1983.Google Scholar
14. Beddoes, T.S. A synthesis of unsteady aerodynamic effects including stall hysteresis, Vertica, 1976, 1, pp 113–123.Google Scholar
15. Beddoes, T.S. Onset of Leading Edge Separation Effects under Dynamic Conditions and Low Mach Number, presented at the 34th Annual National Forum of the American Helicopter Society, Washington DC, USA, May 1978.Google Scholar
16. Beddoes, T.S. Practical computation of unsteady lift, Vertica, 1984, 8, p 55–71.Google Scholar
17. Leishman, J.G. Practical Modelling of Unsteady Airfoil Behaviour in Nominally Attached Two-Dimensional Compressible Flow, UM-AERO-87-6, Department of Aerospace Engineering, University of Maryland, Maryland, USA, 1987.Google Scholar
18. Leishman, J.G. A semi-empirical model for dynamic stall, UM-AERO-87-24, Department of Aerospace Engineering, University of Maryland, USA, 1987.Google Scholar
19. Beddoes, T.S. A Third Generation Model for Unsteady Aerodynamics and Dynamic Stall, Westland Helicopter Limited, RP-908, 1993.Google Scholar
20. Sheng, W., Galbraith, R.A.McD. and Coton, F.N. Refined Dynamic Stall Model for the S809 Aerofoil, to be published.Google Scholar