摘要
采用数值模拟的手段,研究了实体鼓包对超临界翼型的流动控制和减阻作用。超临界机翼在非设计状态时由于波阻增加导致总阻力增大;在激波的波脚位置有效地使用实体鼓包,可以减小激波阻力;在中高升力系数情况下,使用实体鼓包可提高升阻比。
In the paper,numerical simulation methods are used to investigate on action of flow control and wave drag reduction effect with contour bump located on the supercritical airfoil.On the non-design condition,the total drag of the supercritical airfoil increases due to the wave drag heighten.If contour bump is effectively adopted on the supercritical airfoil at the wave feet area,wave drag will be reduced.And under moderate-to-high lift coefficient conditions,contour bump increases the lift-to-drag ratio of the supercritical airfoil remarkably.
出处
《空气动力学学报》
EI
CSCD
北大核心
2010年第4期462-465,共4页
Acta Aerodynamica Sinica
关键词
实体鼓包
减阻
翼型
数值模拟
contour bump
drag reduction
supercritical airfoil
numerical simulation method
