The Annular Aerofoil with Central Body and Propeller: An Approximate Method for the Estimation of the Velocity and Pressure Distribution over the Surface of a Circular Annular Aerofoil with Central Body and Propeller

Abstract

CONSIDER an isolated circular fairing whose cross‐sections along in the flow direction are of aerofoil shape, inclined at small angle of attack a, FIG. 1. By applying the general concept of the aerofoil theory in two‐dimensional flow, it is assumed that the local velocity increment on the surface of annular aerofoil may be considered to be composed of three components v1 v2 and v3, depending on the section thickness and camber and on the angle of attack.

Citation

Pivko, S. (1957), "The Annular Aerofoil with Central Body and Propeller: An Approximate Method for the Estimation of the Velocity and Pressure Distribution over the Surface of a Circular Annular Aerofoil with Central Body and Propeller", Aircraft Engineering and Aerospace Technology, Vol. 29 No. 11, pp. 353-357. https://doi.org/10.1108/eb032894