论文部分内容阅读
数值模拟研究缝道参数对着陆构型多段翼型气动性能的影响,采用有限体积法求解雷诺平均N-S(Navier-Stokes)方程,湍流模型采用S-A(Spalart-Allmaras)模型,给出了多段翼型升力系数与表面压力系数随各缝道参数的变化规律.计算结果表明:采用的计算模型可用于二维多段翼型的计算;缝道参数对多段翼型气动性能的影响显著,在各个缝道参数的变化范围内升力系数均存在最优值,适当的缝道参数可以抑制后翼上表面逆压梯度,消除后翼分离,并保持前翼尾迹不与后翼边界层相掺混,提高多段翼型的气动性能.
Numerical simulations were performed to study the effect of seam parameters on aerodynamic performance of multi-section airfoils with landing configuration. The finite volume method was used to solve the Navier-Stokes equations. The turbulence model was Spalart-Allmaras (SA) Lift coefficient and surface pressure coefficient with the parameters of each seam.The calculation results show that the calculation model can be used for the calculation of two-dimensional multi-section airfoil.The seam parameters have significant influence on the aerodynamic performance of multi-section airfoils, The parameters of lift within the range of the optimal coefficient of existence, the appropriate parameters of the seam can suppress the back surface of the back pressure gradient gradient to eliminate the separation of the rear wing and keep the front wing tail wing boundary layer is not mixed with the rear wing to improve multi-stage Airfoil aerodynamic performance.