Abstract
Abstract : The report describes the analysis in, and the use of, a computer program which has been developed for use in the design of axial compressor airfoils suitable for operation at high subsonic and supersonic Mach numbers. Four rather versatile camber line shapes and two thickness distributions are mathematically derived. These camber lines provide the capability of defining a wide variety of blades, from those of continuously positive camber to the so- called 'S-blades', including many of the intermediate possibilities. A method is presented whereby the airfoils are specified on arbitrary axisymmetric stream surfaces and then accurately redetermined in Cartesian coordinates on planes normal to the stacking axis.
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