摘要
螺旋桨滑流对飞机的升力系数、阻力系数、俯仰力矩系数有着非常重要的影响,该文通过风洞实验方法,探索螺旋桨滑流对飞机气动特性影响的规律。与目前国内常用的全机带动力实验不同,该文结合西北工业大学NF-3低速风洞的翼尖支撑测量系统和螺旋桨及短舱独立支撑机构开展研究,研究了桨叶角、前进比和拉力系数对螺旋桨滑流效果的影响。研究表明:螺旋桨滑流效果主要取决于其拉力系数,飞机升力系数随螺旋桨拉力系数的增大而增大,阻力系数和俯仰力矩系数随螺旋桨拉力系数的增大而减小。
The propeller slipstream has a very important effect on lift coefficients, drag coefficients, and the pitching moment. The effect of propeller slipstream on aerodynamic characteristics is investigated through an experiment method. Differing from the conventional experiment method for a whole airplane with power, the investigation is launched with a combination of a wingtip supporting measuring system in the three dimensional test section of a NF-3 low-speed wind tunnel of Northwestern Polytechnical University and an independent Propeller-Nacelle supporting measuring system. The effect of the propeller slipstream with a propeller blade angle, the advance ratio and thrust coefficient is mainly investigated. This investigation shows that the lift coefficient of an airplane increases with the increase of the propeller thrust coefficient, and both the drag coefficient and the pitching moment decrease with the increase of the thrust coefficient.
出处
《工程力学》
EI
CSCD
北大核心
2013年第7期288-293,共6页
Engineering Mechanics
关键词
螺旋桨
滑流
短舱
风洞实验
翼尖支撑
拉力系数
propeller
slipstream
nacelle
wind tunnel test
wingtip supporting
thrust coefficient
