摘要
本文得出了非定常可压缩升力面情况下直升机悬停时基于前缘吸力的旋翼诱导阻力及功率的计算公式,算例表明了它的适用性,此式可作为优化桨叶平面形状的基础。
A new formula of induced power based on the leading edge suction for a helicopter in hovering is derived in this paper. A simple example shows its applicability. This formula can be used for aerodynamic optimization of rotor blade.
出处
《空气动力学学报》
CSCD
北大核心
1989年第2期258-261,共4页
Acta Aerodynamica Sinica
关键词
直升机
前缘吸力
旋翼
诱导功率
helicopter, leading edge suction, induced power.
