Lift of a Two‐Dimensional Cascade of Aerofoils: Simplified Method of Calculation Based on Schlichting's Theory

Abstract

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.

Citation

Wannenburg, J.J. (1960), "Lift of a Two‐Dimensional Cascade of Aerofoils: Simplified Method of Calculation Based on Schlichting's Theory", Aircraft Engineering and Aerospace Technology, Vol. 32 No. 12, pp. 350-355. https://doi.org/10.1108/eb033338