Wind-Tunnel Setup for Investigations of Normal Shock Wave/Boundary Layer Interaction Control
Wind-Tunnel Setup for Investigations of Normal Shock Wave/Boundary Layer Interaction Control
复制标题
用于研究法向冲击波/边界层相互作用控制的风洞装置
DOI：
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发表时间：
2006
期刊：
影响因子：
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通讯作者：
H. Babinsky
中科院分区：
文献类型：
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作者：
H. Ogawa;H. Babinsky
利用风洞装置研究了正常激波/边界层相互作用的控制。在喷管直流线下游采用宽114 mm、高178 mm的矩形工作截面。为了克服冲击波不稳定性的问题，采用了6mm厚的隔板对进入气流进行隔离。上下通道高度分别保持在91和122 mm。来流边界层厚度为5.7 mm，基于边界层位移厚度的雷诺数约为25000。据观察，冲击可以位于三维隆起和大？分析了前减震腿从驾驶室起始处开始的减震结构。结果表明，风洞装置可用于在传统装置因冲击不稳定而无法容纳冲击系统的位置测试各种类型的冲击控制。
The use of wind-tunnel setup for study of normal shock wave/boundary layer interaction control, was investigated. The rectangular working section that was 114 mm wide, and 178 mm high at the straight downstream of the nozzle was used. The incoming airflow was partitioned by a plate of 6 mm thickness to overcome the problem of shock wave instability. The height of the upper and lower passage was maintained at 91 and 122 mm respectively. The incoming boundary layer thickness was 5.7 mm and the Reynolds number based on boundary-layer displacement thickness was approximately 25,000. It was observed that shock can be located above 3-D bump and large ?-shock structure whose front shock leg starts at the onset of control cab be analyzed. Result shows that wind-tunnel setup can be used to test various types of shock control at positions where conventional setups are unable to hold shock system due to shock instability.