摘要
在FL-26y风洞中利用M1.4喷管和开孔壁试验段进行了实现低超声速流场的实验研究工作。通过实验研究验证了利用M1.4喷管在开孔壁试验段上建立起的低超声速流场的流场品质能够满足国军标合格指标的要求。实验还考察了不同稳定段总压、驻室抽气量等开车参数以及不同试验段扩开角、主流引射缝开度和开孔壁开孔率等洞体条件对流场的影响,为2.4m×2.4m跨声速风洞增设M1.4喷管,拓展该风洞试验马赫数的范围,使其具备M1.4的低超声速试验能力提供了技术支持,同时也为该风洞在下一阶段正式开展M1.4流场调试提供了可供参考的调试参数。
An experimental research of low supersonic flow field for M1.4 nozzle and the perforated wall test section is conducted in the FL-26y wind tunnel.The experimental study has demonstrated that the flow quality of low supersonic flow field in the perforated wall test section established by the use of M1.4 nozzle reaches the qualified requirement in the state and military standard system.The effects on flow field are also considered,for example,the different operation parameters including stagnation pressure and eject flow from the plenum chamber and the different tunnel condition including diffuse angle in the test section,open width for the mainstream ejected slot and porosity of the perforated wall.A M1.4 nozzle is added in 2.4m×2.4m transonic wind tunnel to increase test Mach number range and to provide low supersonic test capability.The calibration parameters for the future M1.4 flow field calibration in this tunnel are also provided.
出处
《实验流体力学》
EI
CAS
CSCD
北大核心
2011年第1期84-87,共4页
Journal of Experiments in Fluid Mechanics
关键词
M1.4喷管
开孔壁
低超声速
实验研究
跨声速风洞
M1.4 nozzle
perforated wall
low supersonic
experimental research
transonic wind tunnel
