Second-order subsonic airfoil theory including edge effects
Second-order subsonic airfoil theory including edge effects
复制标题
包括边缘效应的二阶亚音速翼型理论
DOI：
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发表时间：
1956
期刊：
影响因子：
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通讯作者：
D. Milton
中科院分区：
文献类型：
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作者：
D. Milton
本文将近年来在平面亚音速流动理论方面取得的一些新进展结合成一个统一的二阶理论，适用于任意形状的翼型截面。通过积分求出不可压缩结果，利用二阶可压缩规则将其转化为相应的亚声速可压缩结果，再通过进一步的规则使其在停滞点附近一致有效。给出了一些翼型的解，并与其他理论和实验结果进行了比较。一个直截了当的计算方案概述了计算在任何迎角的任何翼型的表面速度和压力。
Several recent advances in plane subsonic flow theory are combined into a unified second-order theory for airfoil sections of arbitrary shape. The solution is reached in three steps: the incompressible result is found by integration, it is converted into the corresponding subsonic compressible result by means of the second-order compressibility rule, and it is rendered uniformly valid near stagnation points by further rules. Solutions for a number of airfoils are given and are compared with the results of other theories and of experiment. A straight-forward computing scheme is outlined for calculating the surface velocities and pressures on any airfoil at any angle of attack.