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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

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