Approximate theory for the flow through a cascade of cambered airfoils

An approximate theory for steady irrotational flow through a cascade of thin cambered airfoils is developed. Isolated thin airfoils have only slight camber is most applications, and the well known methods that replace the source and vorticity distributions of the curved camber line by similar distributions on the straight chord line are adequate. In cascades, however, the camber is usually appreciable, and significant errors are introduced if the vorticity and source distributions on the camber line are approximated by the same distribution on the chord line.

The calculation of the flow field becomes very clumsy in practice if the vorticity and source distributions are not confined to a straight line. A new method is proposed and investigated; in this method, at each point on the camber line, the vorticity and sources are assumed to be distributed along a straight line tangent to the camber line at that point, and corrections are determined to account for the deviation of the actual camber line from the tangent line. Hence, the basic calculation for the cambered airfoils is reduced to the simpler calculation of the straight line airfoils, with the equivalent straight line airfoils changing from point to point.

The results of the approximate method are compared with numerical solutions for cambers as high as 25 per cent of the chord. The leaving angles of flow are predicted quite well, even at this high value of the camber. The present method also gives the functional relationship between the exit angle and the other parameters such as airfoil shape and cascade geometry.