Smooth Air Inlet and Maximum Lift Conditions for a Cascade of Thin Aerofoils: An Analysis Based on Schlichting's Cascade Theory Showing that for Shock‐Free Inlet Conditions the Angle of Attack must be Zero and that a Symmetrical Camber Line yields the Maximum Lift Coefficient Available to Purchase

SUMMARY Schlichting's cascade functions are expressed as power series in terms of the blade solidity, which makes it possible to derive analytical expressions for the lift coefficient and velocity distribution of an arbitrary cascade of thin aerofoils for solidities of less than unity under smooth air inlet conditions. It is shown that, within the scope of the assumptions made, the angle of attack for shock‐free inlet conditions must be zero, irrespective of the cascade configuration, and that a symmetrical camber line will then yield the maximum lift coefficient. Expressions for this lift coefficient and for the corresponding velocity distribution are derived in terms of the maximum camber and cascade configuration. The analysis is based on Schlichting's cascade theory, and is intended primarily for application to fan blade design.