Analytical Theory of Aeroplanes in Rectilinear Flight and Calculation of the Maximum Cruising Radius

Abstract

Theory of Horizontal Rectilinear Flight of Aeroplanes. Description of underlying basic principles, together with their application to the solution of certain important problems.

Characteristic Relations Connecting the Main Factors Governing the Operation of the Propellers. In these the author expresses practically all functions in terms of slip or functions thereof.

Characteristic Functions and Coefficients of an Aeroplane. These are expressed in terms of weight of the aeroplane, incidence and four specific coefficients which have to be determined by measurement and computation.

Minimum Consumption of Fuel and Oil per Kilometer of Flight. The determinations of consumption which are made are dependent on the altitude of flight; tables are given showing the results of computations for what the author calls the “Aeroplane-Type.”

Cruising Radius of Aeroplanes. Formulœ are given for determining the cruising radius and it is shown that with the present state of aeronautical engineering the cruising radius in still air is theoretically limited to 7000 km. (4350 miles) and that even this can be achieved only by flight at elevations ranging from 16,000 to 25,000 ft.