Foreign Research Progress

Abstract

This report deals with the development of a method which gives a lucid and convenient solution of the flow conditions in the vicinity of a common, thick aerofoil section wherein the thickness of the profile is taken into account. The method consists in making the aerofoil the streamline in a parallel flow by disposing on its mean line certain source and vortex distributions the fields of which are superposed on the parallel flow. These distributions of singularities are secured for the generalized Kármán‐Trefftz profile by means of conformal transformation from the flow about a circle. Five different distribution functions are afforded for the density of superposition, which combine in a specified manner to the necessary distributions of singularity and represent a generalized Kármán‐Trefftz profile in parallel flow. For these profiles the speed for each of the five distributions is then computed independently of the angle of attack.

Citation

(1943), "Foreign Research Progress", Aircraft Engineering and Aerospace Technology, Vol. 15 No. 1, pp. 21-22. https://doi.org/10.1108/eb030982