Range Calculations for Airplanes With Continuously Controllable Pitch Propellers, and the Effect of Certain Geometric Parameters of the Airplane on Range

Citation

Scoles, Albert Buddy and Schoech, William Alton (1938) Range Calculations for Airplanes With Continuously Controllable Pitch Propellers, and the Effect of Certain Geometric Parameters of the Airplane on Range. Master's thesis, California Institute of Technology. doi:10.7907/CMHQ-E314. https://resolver.caltech.edu/CaltechETD:etd-02082006-090132

Abstract

This investigation was undertaken to develop a satisfactorily exact method for the calculation of range of airplane; and with such method, to determine the effect of certain geometrical parameters of the airplane on range, namely, span, aspect ratio, and wing loading.

With satisfactory aerodynamic data from wind tunnel reports, and with satisfactory engine performance data from test stand reports, the method developed permits determination of range, optimum speeds to use, and optimum propeller rpm to use for each speed. It further permits determination of endurance.

In general, increasing aspect ratio for constant span will increase maximum range if reasonable upper limits are placed on wing loading. The gain is but slight for aspect ratios in excess of 11. Similarly, decreasing span for constant aspect ratio will increase maximum range. Both of these variations results in increased wing loading, which can therefore be considered as the fundamental factor giving the increase. There will in general be an optimum combination of aspect ratio and span for a given wing loading which will give maximum range. Satisfactory takeoff and sea-level rate of climb will limit the wing loading; however, for wing loadings in excess of 50, the maximum gain obtainable is of the order of 5%.

Thesis Files