65°三角翼亚音速复杂流场计算和数据可视化

提出一种基于非结构混合网格和有限体积法的有效计算策略,对第二期国际涡流试验项目(second international vortex flow experiment,VFE-2)的尖前缘65°三角翼在马赫数0.4,迎角20.3°,雷诺数2×10~6条件下的亚音速复杂流场结构进行数值模拟,重点探讨了基于计算数据进行该类型复杂涡系干扰表面和空间流场关键特征提取和数据可视化问题.通过与相关试验类比,建立了与先进试验流动显示技术相比拟的定性和定量分析方法,为三角翼这类复杂流场结构的精细分析奠定了技术基础.采用上述方法,细致分析了亚音速三角翼的大迎角复杂旋涡流场结构,得到了与试验一致的结论.研究证实:在大迎角条件下,三角翼流动物理复杂,黏性效应耦合严重,只有通过N-S方程计算才能准确地捕捉主涡和二次涡的发展.

NUMERICAL SIMULATION AND VISUALIZATION OF COMPLEX SUBSONIC FLOW OVER A 65°DELTA WING

The VFE-2 65° delta wing with sharp leading edge in subsonic flows at Mach number of0.4,angle of attack of 20.3°,and Reynolds number of 2 × 106 is numerically simulated by using an unstructured hybrid mesh based finite volume method,with emphasis on how to extract the key flow features for visualization both on surface and in space for such type of complex flows.Approaches for the advanced flow visualization techniques are used for qualitative and quantitative analyses,as a solid foundation for elaborated analysis of complex flow structures of delta wing.With these approaches,the complex vortex flow structure of the subsonic delta wing at high angle of attack is analyzed,and results are consistent with experiments.It is shown that the flow over delta wing at high angle of attack has a complex physical nature with a strong viscous coupling effect,and the evolutions of the primary and secondary vortices can be accurately captured only by a Navier-Stokes equation based simulation.