Chordwise Loading and Camber for Two-Dimensional Thin Sections.

摘要

Derivations are given for the calculation of section camberline from a given segmented chordwise load distribution, and for the inverse problem. In both cases, the algorithms are exact within the limits of thin-wing theory. This document is concerned with two-dimensional, thin, lifting sections and gives the derivation of the camberline from a segmented chordwise loading (the design problem) and the calculation of loading from a discretely-defined camberline (the analysis problem). To the author's knowledge, these derivations have not been published for the general case, although the results for some specific cases are well known, good examples are the NACA a-series camberlines, obtained from simple two-segment load distributions, which have been widely used for many years. Keywords: Canada; Aerodynamics; Aircraft wings. (JES)