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Published online by Cambridge University Press: 28 July 2016
The theoretical aerodynamic properties of supersonic aerofoils of polygonal section are well known. This note describes the results obtained by applying supersonic aerofoil theory to a simple curved aerofoil of arbitrary maximum thickness position, the leading and trailing edges of which are pointed.
The results for a symmetrical curved section are compared with the theoretical properties of a symmetrical double-wedge section.