冲压增程弹用进气道试验与数值研究

对某冲压增程弹用超声速双锥进气道流场特性进行研究,在风洞试验中得到合理的流场结构图谱及试验数据.采用块结构网格与二阶精度流场分区求解技术,对该超声速进气道内外流场进行数值研究.通过数值模拟得到了对应于不同出口反压和攻角情况下,超声速进气道内外粘性流场复杂的波系结构,分析了进气道内外流场的形成过程.结果表明:数值模拟得到的流场结构波系图与风洞试验纹影图一致,并且进气道扩压段静压分布以及进气道出口位置的总压分布与试验结果基本一致.

Experimental and Numerical Research on Inlet of Ramjet Assisted Range Projectiles

Flow characteristic of supersonic bicone inlet of ramjet assisted range projectiles is studied, and reasonable flow structures are also achieved through the wind tunnel experiment. Applying block structure grid and second-order zonal solver method, the numerical research on this inlet is presented. Complex wave structures of supersonic inlet at different backflow pressure and angle of attack are achieved by numerical simulation. The developing progress of internal and external flow structure of inlet is analyzed. Results show that it is almost coincident of numerical flow structure with wind tunnel experimental structure, and the distribution of static pressure at divergent section of inlet and total pressure at exit of inlet is also coincident compared with experimental results.