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A theoretical model for predicting the performance of circulation controlled aerofoils and cascades

Published online by Cambridge University Press:  04 July 2016

W. L Flint  and
C. I Holliday
W. L Flint
Affiliation:
Dept of Mechanical Engineering, The University of Aston in Birmingham
C. I Holliday
Affiliation:
Smiths Industries Aerospace and Defence Systems Co., PutneyDivision
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Summary

The procedure described applies to aerofoils or cascades with circulation controlled by tangential blowing jets and provides a complete numerical solution for aerodynamic performance in incompressible flow conditions.

The pressure distribution over the blade surface is predicted by a potential flow model in which the region of separated flow is represented by an appropriated source distribution. Boundary layer development is calculated by a finite-difference solution of the parabolic boundary layer momentum equation: the development of the blowing jet and its mixing with the boundary layer over the curved trailing edge is predicted by the same procedure applied to an angular momentum equation, using an intermittency representation of the eddy viscosity distribution.

Predictions are compared with experimentally measured lift coefficients for an isolated aerofoil, with turning angles for a cascade tested by other workers and with experimental turning angles for a cascade tested by the authors. The agreement between theory and experiment is good.

Type
Research Article
Information
The Aeronautical Journal , Volume 86 , Issue 852 , February 1982 , pp. 76 - 82
Copyright
Copyright © Royal Aeronautical Society 1982 

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