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On the application of linearised theory to multi-element aerofoils Part II: Effects of thickness, camber and stagger

Published online by Cambridge University Press:  04 July 2016

G. D. Watt  and
G. V. Parkinson
G. D. Watt
Affiliation:
Defence Research Establishment, Atlantic, Dartmouth, Nova Scotia, Canada
G. V. Parkinson
Affiliation:
Department of Mechanical Engineering, University of British Columbia, Vancouver, Canada
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Summary

A linearised two-dimensional incompressible potential flow theory for two-element aerofoil sections is developed. It is capable of predicting the effects of angle of attack, flap deflection, camber, thickness, stagger and overlap of aerofoil elements on the forces. These effects are summarised in integrals which are analogous to the one-element thin aerofoil theory Munk integrals. Analytical expressions for the forces on tandem NACA 23012 aerofoils have been derived and results are presented. Comparisons are also made with a realistic slotted flap configuration with overlap for which experimental data is available. The linearised theory is seen to correlate with these real flow results as well as and better than it does in the one-element regime.

Type
Research Article
Information
The Aeronautical Journal , Volume 90 , Issue 899 , November 1986 , pp. 339 - 356
Copyright
Copyright © Royal Aeronautical Society 1986 

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References

1. Watt, G. D. and Parkinson, G. V. On the application of linearised theory to multi-element aerofoils. Part I: Tandem flat plate aerofoils. Aeronautical Quarterly, February 1983, 34.Google Scholar
2. Watt, G. D. Multi-element thin airfoil theory. PhD thesis, University of British Columbia, December 1984.Google Scholar
3. Glauert, H. The elements of aerofoil and airscrew theory. Cambridge University Press, 1926.Google Scholar
4. Stewart, H. J. A simplified two-dimensional theory of thin aerofoils. Journal of Aeronautical Sciences, 1942, 9, 12, 452–456.Google Scholar
5. Sedov, L. I. Two-dimensional problems in hydrodynamics and aerodynamics. John Wiley and Sons, 1965. Translation.Google Scholar
6. Richardson, J. R. Aerodynamic forces on perforated bridge decks. National Maritime Institute, R. 118, England, 1981.Google Scholar
7. Munk, M. M. General biplane theory. NACA Rpt 151, 1922.Google Scholar
8. Millikan, C. B. An extended theory of thin airfoils and its application to the biplane problem. NACA Rpt 362, 1930.Google Scholar
9. Garrick, I. E. Potential flow about arbitrary biplane wing sections. NACA Rpt 542, 1936.Google Scholar
10. Abbott, I. H. and Von Doenhoff, A. E. Theory of wing sections. Dover publications, New York, 1959.Google Scholar
11. Brown, G. P. and Parkinson, G. V. A linearised potential flow theory for airfoils with spoilers. J Fluid Mech, 1973, 57, part 4, 695–719.Google Scholar
12. Abbott, I. H. and Greenberg, H. Tests in the variable density wind tunnel of the NACA 23012 airfoil with plain and split flaps. NACA Rpt 661, 1939.Google Scholar
13. Foster, D. N., Irwin, H. P. A. H. and Williams, B. R. The two-dimensional flow around a slotted flap. ARC RM 3681, 1970.Google Scholar