上缘开缝翼伞模型风洞试验方法探索研究

Research on Wind Tunnel Test Method of Model of Slit Parafoil at Upper Edge

以PD170型翼伞为原型伞的半刚半柔型开缝翼伞模型为研究对象,利用高精度六分量天平测试系统测试其在不同姿态角和扰流缝结构开度情况下的气动力,利用"丝线法"获取不同扰流缝结构开度的上翼面流谱图,研究了开缝翼伞模型不同开缝度的升阻力特性和翼面流场特性,丰富了多元化冲压翼伞的风洞试验技术。

A semi-rigid and semi-flexible slotted parafoil model of PD170 parafoil was taken as the research object. The aerodynamic force of the model was tested under different attitude angles and the opening of the spoiler structure by using a high precision six-component balance test system. By using the "silk flow spectrum method", the flow patterns of the upper wing with different openings of the slits were obtained. The lift-drag characteristics and the flow field characteristics of the wing with different slits were found out. The wind tunnel test technology of the diversified punching parafoil was enriched.