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The effect of trailing edge extensions on the performance of the Göttingen 797 and the Wortmann FX 63-137 aerofoil sections at Reynolds numbers between 3 x 105 and 1 x 106

Published online by Cambridge University Press:  04 July 2016

A. Ito
A. Ito*
Affiliation:
College of AeronauticsCranfield Institute of Technology
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Summary

The effect of trailing edge extensions was tested for the twodimensional Göttingen 797 and Wortmann FX 63-137 aerofoil sections with smooth surfaces at chord Reynolds numbers from 3 x 105 to 1 x 106 in the 8ft x 6ft low speed wind-tunnel at the Cranfield Institute of Technology. Force measurements were made on the basic aerofoil sections and with extension plates of 10% and 20% chord set tangential to the upper surface at the trailing edge. It was verified that the addition of an extension plate effectively brings about an increase of maximum lift coefficient and an improved lift-to-drag ratio for the Göttingen aerofoil section. However, the effect of the extension plate was small on the Wortmann aerofoil section.

Type
Research Article
Information
The Aeronautical Journal , Volume 93 , Issue 928 , October 1989 , pp. 283 - 289
Copyright
Copyright © Royal Aeronautical Society 1989 

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Footnotes

p1

Permanent address: Department of Mechanical Engineering, School of Science and Technology, Meiji University, 1-1-1, Higashi-Mita, Tama-ku, Kawasaki 214, Japan.

References

1. Yamana, M. and Ito, A. On the wing sections with high maximum lift coefficient. Trans Jpn Soc Aeron Space Sci, 1977, 25. (279), 201–207.Google Scholar
2. Bastedo, W. G. Jr and Muller, T. J. Spanwise variation of laminar separation bubbles on wings at low Reynolds numbers. J Aircr, Sept 1986, 23, 687–694.Google Scholar
3. Marchman, J. F. Aerodynamic testing at low Reynolds numbers, J Aircr. Feb 1987, 24, 107–114.Google Scholar
4. Sun, Z., Sumantran, V. and Marchman, J. F. An examination of low and environmental effects on chordwise pressure distribution data for a finite Wortmann wing at low Reynolds numbers. Department of Aerospace and Ocean Engineering, Virginia Polytechnic Institute and State University, Blacksburg, July 1985.Google Scholar
5. Marchman, J. F. III and Sumantran, V. Control surface effects on the low Reynolds number behaviour of the Wortmann FX 63-137. Proceedings of International Conference on Aerodynamics at Low Reynolds Numbers 104 < Re < 106. The Royal Aeronautical Society, Oct 1986, 11.1-11.14.Google Scholar
6. Render, P. M. Airfoil Measurements at Low Reynolds Numbers, CoA Report No 8508, Cranfield, May 1985.Google Scholar
7. Davidson, C.J. The experimental investigation of the effects of roughness upon airfoil characteristics at low Reynolds numbers. MSc Thesis, Cranfield Institute of Technology, Cranfield, September 1985.Google Scholar
8. Dyer, D. J. and Stollery, J. L. Preliminary measurements of the flight performance of an RPV compared with wind tunnel and CFD estimates. Proceedings of International Conference on Aerodynamics at Low Reynolds Numbers 104 < Re < 106. The Royal Aeronautical Society, October 1986, 29.1-29.14.Google Scholar
9. Pope, A. and Harper, J. J. Low-Speed Wind Tunnel Testing. Wiley and Sons, New York, 1966.Google Scholar