Abstract
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.
Publisher
Cambridge University Press (CUP)
Reference6 articles.
1. Lakshminaravana B. and Horlock J. H. Tip Clearance Flow and Losses for an Isolated Compressor Blade. ARC R&M 3316, 1963.
2. Prandtl L. and Betz Z. Vier Abhandlungen zur Hydro- dynamik und Aerodynamik, p. 52. Selbstverlag des Kaiser Wilhelm-Instituts fur Stromung Forschung. Gottingen, 1927.
3. Bollay W. A Non-Linear Wing Theory and Its Application to Rectangular Wings of Small Aspect Ratio. ZAMM. Bd 19, No. 1, 1939.
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3 articles.
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