跨声速风洞高速段一体化数值模拟研究

追求高亚声速经济巡航的民机、跨声速高机动特性的战斗机对高性能跨声速风洞的需求日趋紧迫,开 展跨声速风洞高速段一体化数值模拟研究,对跨声速风洞设计具有一定的参考意义。通过非对称平板扩压器 算例,初步验证计算方法的可行性,并对跨声速风洞高速段进行计算收敛评判方法、不同初始条件和槽壁扩张 角等因素研究。结果表明:采用模型区前后两个监测点马赫数变化作为收敛判据,方法可行且模型区流场均 匀;不同初始化条件对收敛结果总体影响较小,特别是各截面流场分布和槽道流动方向上,两者结果基本相同; 跨声速状态槽壁扩张角0.3°得到的试验段模型区域流场品质较槽壁扩张角0.0°更均匀。

Numerical Simulation of High-Speed Section in Transonic Wind Tunnel

As the aerospace vehicle gradually enters the era of refined design, especially for civil aviation aircraft with high subsonic economic cruising and fighters with high maneuverability at transonic speed, the demand for high-performance transonic wind tunnels is becoming more and more urgent, and the numerical simulation of the high-speed section of the tunnel has certain reference significance for the design of transonic wind tunnel. Therefore, an 8.50 plane asymmetric diffuser has been calculated firstly, the separation and reattachment points agree with the experiment; Secondly, the convergence criterion, initial condition and slotted wall divergence angle of high-speed section for transonic wind tunnel have been considered, the results indicated that the mach number of monitoring points in model section has represented numerical convergence. Also, the influence on velocity distri-bution at model section and streamline in slot with different initial conditions is negligible. Moreover, the slotted wall divergence angle 0.3° has acquired more uniform flow fields than divergence angle 0.0°.