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三角翼是涡发生器的主要结构型式,用于涡发生器的三角翼常处于翼面边界层内。本文采用数值求解雷诺平均NS方程的方法,以平板上一个三角翼模型为研究对象,研究不同来流边界层速度型(均匀分布、湍流边界层速度型和层流边界层速度型)和5种边界层厚度条件下,三角翼诱导涡沿流向的最大涡量分布规律及衰减规律。结果表明,湍流边界层下三角翼诱导涡最大涡量值要大于层流边界层,且边界层高度越低,诱导涡最大涡量值越大。
Triangular wing is the main structure of the vortex generator, the delta wing for the vortex generator often in the airfoil boundary layer. In this paper, a numerical solution to the Reynolds-averaged Navier-Stokes equations is used to investigate the effects of different velocity boundary layer velocity models (uniform distribution, turbulent boundary layer velocity and laminar boundary velocity) and five Under the condition of boundary layer thickness, the maximum vorticity distribution and attenuation law of delta vane induced vortex flow direction are presented. The results show that the maximum vorticity of the induced vortex under the turbulent boundary layer is larger than that of the laminar boundary layer, and the lower the boundary layer height is, the larger the maximum vorticity value of the induced vortex is.