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对带气室的展弦比为3的不同平面形状翼伞模型的流场进行了三维定常数值模拟,详细考察了平面形状对翼伞气动性能的影响。运用有限体积法对三维坐标系下不可压雷诺时均Navier-Stokes(RANS)方程进行了直接求解,采用剪切应力输运(SST)k-ω二方程湍流模型进行湍流模拟。数值模拟得出的原始翼伞的气动性能参数与试验数据在总趋势上符合很好,多种平面形状的翼伞模型计算结果表明:椭圆形翼伞模型获得最小阻力系数,前缘切口改变了上下缘流态使其升力系数并非最大;前缘后掠能明显减小翼伞阻力;由于翼伞中部区域对有效升力贡献更大,前缘后掠的翼伞模型获得最大升阻比;阻力对翼伞升阻比影响很大,前缘切口阻力是总阻力的主要来源之一,且是一种二维效应的阻力。该文可为进一步研究更多不同几何参数的翼伞模型提供参考。
The three-dimensional numerical simulation of the flow field of a parafoil model with airfoil with an aspect ratio of 3 was carried out. The effects of the plane shape on the aerodynamic performance of the parafoil were investigated in detail. The finite volume method is used to directly solve the incompressible Reynolds-averaged Navier-Stokes (RANS) equation in three-dimensional coordinate system. The turbulent model is simulated by two-equation turbulent flow model of shear stress transport (SST) k-ω. The aerodynamic performance parameters and experimental data of the original wing parachute obtained by the numerical simulation are in good agreement with the general trend. The calculation results of the parafoil models with various planar shapes show that the minimum drag coefficient is obtained for the elliptical wing parachute model, and the leading edge incision is changed The lift coefficient of the upper and lower edge is not the maximum; the leading edge swept can significantly reduce the wing parachute drag; wing parachute model gain the maximum lift-drag ratio as the mid-wing contribute more to the effective lift; resistance On the parachute lift resistance ratio is greatly affected, leading edge incision resistance is one of the main sources of total resistance, and is a two-dimensional effect of the resistance. This article can provide reference for further research on wing parafoil models with different geometric parameters.