Abstract:
By a modification of the method used to calculate the profile drag of aerofoils a method has been developed for calculating the drag of smooth bodies of revolution. This method has been applied to three bodies at zero incidence, the calculations covering a wide range of fineness ratio, Reynolds number and transition position. It is hoped that the results of these calculations will be of particular value to those engaged in performance estimation and in research relating to the cleanness efficiency of aeroplanes.
