A method is presented by means of which the lift coefficient of an arbitrary aerofoil in a two-dimensional cascade is obtained explicitly in terms of a number of cascade functions, whose values depend only on the cascade geometry. The method is based on Schlichting's theory, whereby the profile is substituted by a continuous row of singularities arranged along the blade chord, and it consists in a simplification of the usual procedure of satisfying the boundary conditions. The simplified method greatly reduces the amount of work involved, and an analysis of a number of representative aerofoils indicated a good agreement with the values obtained by the more exact procedure. The values of the special cascade functions required for the application of the method are tabulated over a wide range of stagger angles and pitch/chord ratios.
Lift of a Two-Dimensional Cascade of Aerofoils
Simplified Method of Calculation Based on Schlichting's Theory
Aircraft Engineering and Aerospace Technology ; 32 , 12 ; 350-355
1960-12-01
6 pages
Article (Journal)
Electronic Resource
English
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