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本文对λ=5,η=1、(?)=10%,前、后掠角分別为45°的机翼,在迎角α=0°～70°范围内进行了低速纵向特性的实验研究。为了深入了解气动特性,除了测量力和力矩外,还做了油流和烟流实验。实验发现,后掠翼在α=25°～30°、前掠翼在α=50°～55°范围内,气动特性出现异常变化(阻力不随迎角改变,升力急剧下降,力矩曲线斜率反向),并发现在较大迎角时机翼后缘出现后缘涡。文中除了比较和分析前、后掠机翼气动特性外,对气动特性的异常变化和后缘涡都作了说明或讨论。
In this paper, the low-speed longitudinal characteristics of the airfoil with λ = 5, η = 1, (?) = 10% and the front and back sweep angles are 45 ° were studied in the angle of attack α = 0 ° ~ 70 ° . In order to understand the aerodynamic characteristics in depth, in addition to measuring the force and torque, but also made the oil flow and smoke experiments. The experimental results show that the aerodynamic characteristics of the swept-back wing vary from α = 25 ° to 30 ° with the forward swept wing in the range of α = 50 ° to 55 ° (the resistance does not change with the angle of attack, the lift drops sharply, and the slope of the torque curve is reversed ) And found a trailing vortex at the trailing edge of the wing at a larger angle of attack. In addition to comparing and analyzing the aerodynamic characteristics of the front and back sweep wings, the anomalous changes in the aerodynamic characteristics and the trailing vortices are all described or discussed in this paper.