基于轴线马赫数分布的喷管扩张段无粘型面设计

摘要

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 distri-bution method was proposed.The designed nozzle characteristic network was triangulated and compared with the numerical simulation result,and influencing factors were analyzed for the noz-zle 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 characteris-tic point distribution and the amount of characteristic points on the boundary.