| 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 and securely checking the prepared aerofoil profile. SOLUTION: This program and method for preparing the aerofoil profile are formed so that a blade thickness definition expression comprises a first function ( tertiary function) defining the leading edge blade thickness function on the leading edge side of the maximum blade thickness point and a second function (tertiary function) defining the trailing edge blade thickness function on the trailing edge side of the maximum blade thickness point. In the first function and the second function, a blade thickness value is calculated, and the calculated value is compared with a set maximum blade thickness value and checked whether it is larger than the maximum blade thickness value or not. Also, by differentiating the first function and the second function, it is checked whether or not there is a maximum or minimum point or inflection point at those positions other than the set position of the maximum blade thickness. COPYRIGHT: (C)2006,JPO&NCIPI
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