| 张有1，吴锋1，2，冯旭栋1，尹骥1.1 种副孔正交型超声速5 孔探针的设计与应用[J].航空发动机,2018,44(5): |
| 1 种副孔正交型超声速5 孔探针的设计与应用 |
| Application and Research of a Supersonic Five-Hole Probe with Orthogonal Ancillary HolesZHANG |
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| DOI： |
| 中文关键词: 超声速5 孔探针 风洞校准 数值分析 射流 航空发动机 |
| 英文关键词:supersonic five-hole probe wind tunnel calibration numerical analysis jet aeroengine |
| 基金项目:国家自然科学基金（51506108）资助 |
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| 中文摘要: |
| 针对超声速喷管出口流场Ma 和方向角的测量，设计了直径为4 mm 的副孔正交型超声速5 孔探针。圆锥形测压头半角
为20毅，测压孔直径为0.4 mm，探针直段长140 mm。分别在亚声速风洞（196 个校准点）和超声速风洞（294 个校准点）中对5 孔探针
进行了校准，结果表明：5 孔探针在不同Ma 下的方向特性曲线具有几何相似性，有较高的角度灵敏度；总压特性系数和静压特性系
数均具有良好的对称性。并通过数值计算研究了5 孔探针的扰流特性。结合自动位移机构，完成了超声速喷管出口5 个截面共315
个坐标点的标定，获得了流场的Ma 和方向角分布特性 |
| 英文摘要: |
| An orthogonal supersonic five-hole probe with a diameter of 4 mm was designed for the measurement of Mach number and
direction angle of flow field at the outlet of supersonic nozzle. The half angle of conical measuring pressure head was 20o,the diameter of
pressure hole was 0.4 mm,the length of straight section of probe was 140 mm. The five-hole probe was calibrated respectively in subsonic
wind tunnel (196 calibration points)and supersonic wind tunnel (294 calibration points). The results show that the directional
characteristic curves of five-hole probe at different Mach number has geometric similarity and high angle sensitivity. Both the total pressure
characteristic coefficient and the static pressure characteristic coefficient have good symmetry. The scrambling characteristics of the probe
with five -hole are studied by numerical calculation. Combined with the automatic displacement mechanism,the calibration of 315
coordinate points with five sections at the outlet of the supersonic nozzle are completed,and the Mach number and direction angle
distribution characteristics of the flow field are obtained. |
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