| 摘要 |
PROBLEM TO BE SOLVED: To provide a program and a method for preparing an aerofoil profile capable of changing a plurality of design factors determining the cross sectional profile of a blade (aerofoil) on the leading edge side and trailing edge side of a blade thickness function independently of each other when the aerofoil is changed (adjusted). SOLUTION: This program and method for preparing the aerofoil profile are formed so that a blade thickness definition expression expressing the change of a blade thickness defined on the cross section of an aerofoil profile comprises a tertiary function as a first function defining the leading edge blade thickness function on the leading edge side of the maximum blade thickness point of the blade thickness function and a tertiary function as a first function defining the leading edge blade thickness function on the trailing edge side of the maximum blade thickness point of the blade thickness function. The camber line length of the cross section of the aerofoil profile, the position of the maximum blade thickness, the maximum blade thickness value, a leading edge blade thickness change rate, a trailing edge blade thickness change rate, a leading edge blade thickness value, and a trailing edge blade thickness value are defined as design factors. The first and second functions comprise boundary conditions tangentially continued to each other at the maximum blade thickness point. COPYRIGHT: (C)2006,JPO&NCIPI
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