基于轴线马赫数分布的喷管扩张段无粘型面设计

Design of nozzle inviscid contour based on axial Mach number distribution

针对高超声速风洞轴对称喷管设计问题,开展了喷管扩张段无粘型面设计研究。介绍了基于预设轴线马赫数分布的直接设计方法,改进了基于面积比的轴线马赫数分布预设方法,提出了一种方便多点控制的轴线特征点分布方法。对设计喷管流场进行特征线网三角化,与数值模拟结果进行比较,并分析了影响喷管无粘型面的设计因素。表明:改进的面积比方法可以保证轴线马赫数分布预设的合理性;轴线马赫数分布、轴线上特征点分布和边界特征点数明显影响喷管无粘型面。

The supersonic inviscid contour design methods were studied for the hypersonic wind tunnel axial-symmetric nozzle.The Direct-design technique based on the axial Mach number distribution presetting was introduced,the axial Mach number distribution presetting method based on the ratio of area was improved,and a new multipoint-control characteristic point distribution method was proposed.The designed nozzle characteristic network was triangulated and compared with the numerical simulation result,and influencing factors were analyzed for the nozzle inviscid contour.Results indicate that：the feasibility of the axial Mach number distribution presetting method based on the ratio of area is guaranteed by the present improvement;the nozzle inviscid contour is significantly affected by the axial Mach number distribution,axial characteristic point distribution and the amount of characteristic points on the boundary.