摘要
通过数值计算和实验，研究了２１和９火箭发动机燃气喷流流场。数值计算采用激波高分辨率、二阶精度ＴＶＤ格式，得到包括射流边界、桶形激波、反射激波、Ｍａｃｈ盘和滑移线的清晰的流谱。实验测试应用Ｆ－Ｐ激光干涉仪和自动测压系统，得到流场Ｆ－Ｐ干涉照片和压强分布。
Burning gas jet flow fields generated by φ21 and φ9 rocket motor have been investigated both numerically and experimentally. In calculation, a high resolution, second accuracy for shock wave TVD scheme is employed. Clear maps corresponding to the flow fields which include jet boundary, barrel shock, reflected shock, Mach disk and slip line have been obtained. In experimental measurement, F P laser interferometry and auto measurement system are used to take F P interference pictures and test pressure distributions. The computed results are in agreement with the experimental data.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1996年第5期586-589,共4页
Acta Aeronautica et Astronautica Sinica
关键词
火箭
燃气流
数值分析
激光干涉测量
gas streams numerical analysis TVD schemes laser interferometry
