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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.

Using the results of earlier investigations, a method for determination of the velocity or pressure distribution and the aerodynamic properties of a low‐aspect‐ratio swept wing with slender body of elliptical cross‐section and vertical tail surface, having arbtrary form, is briefly presented. The method can be used for the prediction of the load distribution, aerodynamic forces and moments on inclined slender wing, body and vertical tail combinations travelling at subsonic or supersonic speeds.

The operating conditions of a conventional aerofoil type propeller or helicopter rotor in both subsonic and supersonic regions are separately considered, in the absence of direct shock and blade interference effects and other disturbances. The performance of a propeller or rotor is approximately predicted by applying the conventional strip‐type analysis and the results of the two‐dimensional aerofoil theory.

Under this heading are published regularly abstracts of all Reports and Memoranda of the Aeronautical Research Committee, Reports and Technical Notes of the U.S. National Advisory Committee for Aeronautics and publications of other similar research bodies as issued