Andrey V. Boiko, S. V. Kirilovskiy, T. Poplavskaya
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引用次数: 0
摘要
边界层流动的随机化对机翼、短舱和其他在实践中经常遇到的物体的气动特性有显著影响,导致更高的表皮摩擦阻力和更差的气动质量。本研究考虑了在存在二维表面浮雕的情况下遇到向湍流过渡的后掠翼边界层。浮雕的形式是矩形截面的条带,平行于前缘,与前缘的距离不同。计算采用 ANSYS Fluent 18.0 软件和作者基于 eN 方法预测层流-湍流过渡的 LOTRAN 3 软件包进行,攻角为 -5°,入流速度为 30 m/s。文中给出了受表面浮雕影响的后掠翼横流不稳定性 N 因子分布的新数据。这些数据对于过渡的工程建模具有重要的实际意义。此外,还显示了利用浮雕作为被动方法削弱横流不稳定性达 30% 以延缓流动随机化的有效性。
Numerical Simulation of Swept-Wing Laminar–Turbulent Flow in the Presence of Two-Dimensional Surface Reliefs
Stochastization of boundary-layer flow has a dramatic effect on the aerodynamic characteristics of wings, nacelles, and other objects frequently encountered in practice, resulting in higher skin-friction drag and worse aerodynamic quality. A swept-wing boundary layer encountering a transition to turbulence in the presence of two-dimensional surface reliefs is considered. The relief has the form of strips of a rectangular cross-section oriented parallel to the leading edge and located at different distances from it. The computations are performed for the angle of attack of −5° and an incoming flow velocity of 30 m/s using the ANSYS Fluent 18.0 software together with the author’s LOTRAN 3 package for predicting the laminar–turbulent transition on the basis of the eN-method. New data on distributions of N factors of swept-wing cross-flow instability affected by the surface relief are presented. The data are of practical importance for engineering modeling of the transition. Also, the effectiveness of using the reliefs as a passive method of weakening the cross-flow instability up to 30% to delay the flow stochastization is shown.