METHOD FOR PREDICTING THE PRESSURE DISTRIBUTION ON SWEPT WINGS WITH SUBSONIC ATTACHED FLOW.

被引：0
|
作者：
Anon
机构：
来源：
Engineering Sciences Data Unit, Data Items | 1973年
关键词：
D O I：
暂无
中图分类号：
学科分类号：
摘要：
ESDU 73012 presents an equation for the velocity at any point on the surface of a wing in compressible or incompressible subcritical flow. The formula applies for thickness/chord ratios up to 20 per cent, camber up to 3 per cent of chord, aspect ratios greater than 2. 5 and equivalent sweeps less than 60 degrees. No boundary layer calculation is included. The physical significance of the various terms in the equation is explained, and tables and graphs give values for them to assist in calculating answers rapidly.
引用
收藏
相关论文
共 50 条
12345