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An investigation of dynamic stall onset on a pitching wing

Published online by Cambridge University Press:  04 July 2016

A. Ferrecchia ,
F. N. Coton ,
R. A. McD. Galbraith  and
R. B. Green
A. Ferrecchia
Affiliation:
University of Glasgow, Glasgow, UK
F. N. Coton
Affiliation:
University of Glasgow, Glasgow, UK
R. A. McD. Galbraith
Affiliation:
University of Glasgow, Glasgow, UK
R. B. Green
Affiliation:
University of Glasgow, Glasgow, UK
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Abstract

This paper presents an examination of dynamic stall onset on both a rectangular wing and a nominally two-dimensional aerofoil with the same cross-section. The intention is to determine the extent to which the onset of dynamic stall is changed in the three-dimensional case. To do this, three different criteria are applied to measured pressure data to identify both the onset of the stalling process and the formation of the dynamic stall vortex. It is shown that examination of the vorticity flux in the vicinity of the leading edge provides a means of determining vortex formation in the absence of strong three-dimensional effects. It is also shown that this technique is not applicable on outboard sections of the rectangular wing where the phasing of dynamic stall onset with respect to the leading edge response is altered by the three-dimensionality of the flow. It is concluded that the application of two-dimensional stall onset criteria is inappropriate under such conditions.

Type
Research Article
Information
The Aeronautical Journal , Volume 107 , Issue 1074: University of Glasgow 50th year anniversary special , August 2003 , pp. 487 - 494
Copyright
Copyright © Royal Aeronautical Society 2003 

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References

1. Carr, L.W. Progress in analysis and prediction of dynamic stall. J. Aircr, January 1988, 25, (1).Google Scholar
2. McCroskey, W.J., Carr, L.W. and McAlister, K.W. Dynamic stall experiments on oscillating airfoils, AIAA J, 1976, 14, (1).Google Scholar
3. 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 Soc, 1981, 13, (1).Google Scholar
4. Gracey, M.W., Niven, A.J. and Galbraith, R.A.McD. A consideration of low-speed dynamic stall onset, 15th European Rolorcraft Forum, Amsterdam, 1989.Google Scholar
5. Leishman, J.G. and Beddoes, T.S. A semi-empirical model for dynamic stall, J American Helicopter Society, July 1989.Google Scholar
6. Gangwani, S.T. Synthesised airfoil data method for prediction of dynamic stall and unsteady airfoils. Vertica, 1984, 8.Google Scholar
7. Tran, C.T. and Petot, D. Semi-empirical model for the dynamic stall of airfoils in view of the application to the calculation of responses, ONERATP 103-1980.Google Scholar
8. Coton, F.N., Galbraith, R.A.McD. and Green, R.B. The effect of wing planform shape on dynamic stall. Aeronaut J, March 2001. 105, (1045), pp 151–159.Google Scholar
9. Anoell, R.K. Musqrove, P.J. and Galbraith, R.A.McD. Collected data for tests on a NACA 0015 aerofoil., 1, 2 & 3, GU Aero Report 8805,1988.Google Scholar
10. Coton, F.N. and Galbraith, R.A.McD. An experimental study of dynamic stall on a finite wing. Aeronaut J, May 1999, 103. (1023), pp 229–236.Google Scholar
11. Gracey, M.W., Niven, A.J., Coton, F.N., Galbraith, R.A.McD. and Jiang, D. A correlation indicating incipient dynamic stall. Aeronaut J, 1996, 100. (997), pp 305–311.Google Scholar
12. Scruggs, L.Y., Nash, J.F. and Singleton, R.E. Analysis of dynamic stall using unsteady boundary layer theory, NASA CR 2462, 1974.Google Scholar
13. McCullough, G.B. and Gault, D.E. Examples of three representative types of aerofoil section stall at low speed, NACA TN 2502. 1951.Google Scholar
14. Tani, I. On the design of airfoils in which the transition of the boundary layer is delayed. Appendix: Transition caused by laminar separation, NACA TM 1351, 1952.Google Scholar
15. Owen, P.R. and Klanfer, L. On the laminar boundary layer separation from the leading edge of a thin aerofoil, ARC CP 220. 1953.Google Scholar
16. Evans, W.T. and Mort, K.W. Analysis of computed flow parameters for a set of sudden stalls in low-speed two-dimensional flow, NASA TND-85, 1959.Google Scholar
17. Seto, L.Y. and Galbraith, R.A.McD. The effect of pitch rate on the dynamic stall of a NACA 23012 aerofoil., Proceedings of the Eleventh European Rotorcraft Forum. London, September, 1985.Google Scholar
18. Acharya, M. and Metwally, M.H. Unsteady pressure field and vorticity production over a pitching aerofoil, AIAA J, 1992, 30, pp 403–411.Google Scholar
19. Green, R.B. and Galbraith, R.A.McD. Dynamic stall vortex convection: thoughts on compressibility effects. Aeronaut J, 1996, 100. (999). pp 367–372.Google Scholar
20. Lighthill, M.J. Introduction to boundary layer theory, in Laminar Boundary Layers, Rosenhead, L. (Ed), Oxford University Press, 1963.Google Scholar
21. Reynolds, W.C. and Carr, L.W. Review of unsteady, driven, separated flows, AIAA paper 85-0527, March 1985.Google Scholar
22. Piziali, R.A. 2-D and 3-D oscillating wing aerodynamics for a range of angles of attack including stall, NASA-TM-4632, September 1994.Google Scholar
23. Ashworth, J., Crislet, W. and Luttges, M. Vortex flows created by sinusoidal oscillation of three-dimensional wings, AIAA 7th Applied Aerodynamics Conference, Seattle, 1989.Google Scholar
24. Moir, S. and Coton, F.N. An examination of the dynamic stalling of two wing planforms, Glasgow University Aero Rpt No 9526, 1995.Google Scholar
25. Ferrecchia, A., Coton, F.N. and Galbraith, R.A.McD. An examination of dynamic stall vortex inception on a finite wing and on a NACA 0015 aerofoil, AIAA-99-3112, 17th AIAA Applied Aerodynamics Conference, Norfolk, 1999.Google Scholar
26. Niven, A.J. and Galbraith, R.A.McD. Modelling dynamic stall vortex inception at low Mach numbers, Aeronaut J, 1997, 101, (1002).Google Scholar