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本文对后掠角为70°的尖前缘平板三角形机翼在大冲角和大偏航情况下的流动图案进行了观察。机翼附近涡流场和机翼表面边界层流动的观察, 系分别利用格网丝线术和油膜术进行的。同时, 也测量了表面静压分布。根据这些观测到的数据, 文章分析了在冲角α=0°～30°和偏航角β=0°～30°范围内, α和β对三角形机翼的局部展向静压分布、局部法向力系数和局部滚转力矩系数的影响; 也分析了α和β对主涡核, 附着线, 分离线等位置的影响。
In this paper, we observed the flow pattern of sharp-edged triangular slab with a swept angle of 70 ° at large angle of attack and large yaw. The observation of the eddy current field around the wing and the boundary layer of the wing surface were performed by using mesh wire and oil film respectively. At the same time, the surface static pressure distribution was also measured. Based on these observed data, the local static static pressure distributions of α and β to the triangular wing at α = 0 ° ~ 30 ° and yaw angle β = 0 ° ~ 30 ° are analyzed. Normal force coefficient and local roll torque coefficient; also analyzed the influence of α and β on the position of main vortex core, attachment line and separation line.