摘要
本文提出一种计算模型,用以计算亚声速大迎角下前缘分离机翼的流动和气动特性。通过在涡轴上分布线涡/线汇,这种计算模型包括了对前缘自由涡面、涡核及涡的卷吸作用的模拟。由于它是在非线性离散涡法的基础上发展起来的,因而具有计算过程简捷的特点。对三角翼及双三角翼气动特性的计算表明,计算值与实验值符合得相当好。计算还表明,在计算中计及和不计及涡的卷吸作用能引起计算载荷相当大的变化。
A numerical method for calculating the longitudinal aerodynamic coefficients and the lifting pressure distributions of wings with edge separation is presented.The proposed computed model can include the effects of the vortex core through the simulation with a concentrated line vortex/sink.Good agreement was found between the calculations and the experiments. It was also found that the entrainment effect cf the leading-edge vortex core at high angles of attack should not be neglected in the calculation.
出处
《空气动力学学报》
CSCD
北大核心
1993年第1期10-15,共6页
Acta Aerodynamica Sinica
关键词
数值模拟
细长翼
前缘涡
卷吸作用
numerical simulation, slender wing, leading-edge vortex, entrainment effect.
