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Effects of a Chordwise Gap in an Aerofoil of Finite Span in a Free Stream

Published online by Cambridge University Press:  04 July 2016

B. Lakshminarayana
B. Lakshminarayana*
Affiliation:
Formerly Department of Mechanical Engineering, The University of Liverpool—Now at the Department of Aeronautical Engineering, The Pennsylvania State University, U.S.A.
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Extract

An attempt is made in this note to extend Glauert(1948) analysis to predict the increase in induced drag and decrease in lift due to a split in an aerofoil of finite span placed in a free stream. The values of induced drag obtained from this analysis is compared with Munk and Cario's (1917) experimental values and Prandtl and Betz's (1927) theoretical values. A modified analysis for low gap/length ratio, which takes into account the lift retained at the tip, gives better agreement with Munk's experimental values for gap/length ratio (Ω) less than 0·012. The effect of slot diminishes as the aspect ratio is increased.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 68 , Issue 640 , April 1964 , pp. 276 - 280
Copyright
Copyright © Royal Aeronautical Society 1964

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References

1.Bollay, W. A Non-Linear Wing Theory and Its Application to Rectangular Wings of Small Aspect Ratio. ZAMM. Bd 19, No. 1, 1939.Google Scholar
2.Durand, W. F.Aerodynamic Theory, Vol. IV. Springer Verlag, 1935.Google Scholar
3.Glauert, H.The Elements of Air Screw and Aerofoil Theory. Cambridge University Press, 1948.Google Scholar
4.Lakshminaravana, B. and Horlock, J. H. Tip Clearance Flow and Losses for an Isolated Compressor Blade. ARC R&M 3316, 1963.Google Scholar
5.Munk, M. and Cario, G.Fliigel mit Spalt in Fahrtrichtung. Tech. Berichte der Flug Zeugmeisteri, Vol. 1, p. 219, 1917.Google Scholar
6.Prandtl, L. and Betz, Z. Vier Abhandlungen zur Hydro- dynamik und Aerodynamik, p. 52. Selbstverlag des Kaiser Wilhelm-Instituts fur Stromung Forschung. Gottingen, 1927.Google Scholar