翼型の翼型抗力の計算法
1971 年 19 巻 213 号 p. 445-451
詳細
1971 年 19 巻 213 号 p. 445-451
Methods for calculating the profile drag of airfoils in incompressible and compressible flows are presented respectively. Both methods are constructed by the current. boundany layer theories which have reasonable accuracy. In these method ghe calculated or experimental pressure distributions on airfoils must be given in advance.
Profile drag has been calculated by these methods for several airfoils in both incompressible flow and subcritical subsonic flow at various lift coefficients and Reynolds numbers. Comparison of the results with available experimental data show good agreement.
