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[1]杨博,李龙飞,武建红,等.超音速探针结构对测量精度影响的数值研究[J].火箭推进,2021,47(04):37-45.
　YANG Bo,LI Longfei,WU jianhong,et al.Numerical study on the influence of supersonic pressure probe structure on measurement accuracy[J].Journal of Rocket Propulsion,2021,47(04):37-45.

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超音速探针结构对测量精度影响的数值研究

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 47 期数: 2021年04期页码: 37-45 栏目: 研究与设计出版日期: 2021-08-31

Title:: Numerical study on the influence of supersonic pressure probe structure on measurement accuracy

文章编号:: 1672-9374(2021)04-0037-08

作者:: 杨博¹; 李龙飞²; 武建红³; 马虎^1*; 周胜兵⁴; (1.南京理工大学机械工程学院,江苏南京 210094 2.西安航天动力研究所,陕西西安 710100 3.中国航空工业集团公司北京长城计量测试技术研究所,北京 100095 4.重庆大学航空航天学院,重庆 400044)

Author(s):: YANG Bo¹; LI Longfei²; WU jianhong³; MA Hu^1*; ZHOU Shengbing⁴; (1.School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China 2.Xian Aerospace Propulsion Institute,Xian 710100,China 3.Beijing Great Wall Institute of Metrology and testing technology,AVIC,Beijing 100095,China 4.College of Aerospace Engineering,Chongqing University,Chongqing 400044,China)

关键词:: 数值模拟总压探针静压探针超音速

Keywords:: numerical simulation total pressure probe static pressure probe supersonic

分类号:: O354.3

文献标志码:: A

摘要:: 为探讨超音速来流中总压、静压探针的开口形式对其测量精度的影响,获得高精度的总压、静压探针结构参数,采用FLUENT商业软件研究了内倒角、半球头、外倒角三种开口形式的总压探针在七种来流马赫数及三种来流偏角条件下的性能和三种开口形状的静压探针在七种来流马赫数条件下的性能。研究结果表明,数值模拟结果与风洞实验结果吻合较好,验证了数值方法的可靠性。数值模拟结果与理论值对比表明:总压探针对流场扰动程度的大小与总压探针精度正相关外倒角型总压探针对安装偏角的不敏感性最好,相对误差未超过1.5% 外倒角型总压探针的倒角大小对于外倒角型总压探针的性能几乎没有影响给定的条件下,静压探针使用0.2D的测孔、15°的斜孔角度可以得到精度较高的结果。

Abstract:: The objective is to explore the influence of the opening form of the total pressure probe and static pressure probe in the supersonic flow on its measurement accuracy,and to obtain the high-precision total pressure probe and static pressure probe structure parameters.In this paper,FLUENT commercial software is used to study the performance of the total pressure probe with three opening forms:inner chamfer,hemispherical head,and outer chamfer under the conditions of seven incoming flow Mach numbers and three incoming flow deflection angles.In addition,the performance of three open-shaped static pressure probes under seven flow Mach number conditions is studied.The research results show that the numerical simulation results are in good agreement with the wind tunnel experimental results,which verifies the reliability of the numerical method.The comparison between the numerical simulation results and the theoretical value shows that the disturbance degree of the flow field by the total pressure probe is positively correlated with the accuracy of the total pressure probe.The total pressure probe with external chamfer has the best insensitivity to the installation deflection,and the relative error is less than 1.5%.The chamfer size of the total pressure probe with external chamfer has almost no effect on itsperformance.Under the conditions given in this article,the static pressure probe with a 0.2D measuring hole and a 15°angle of inclined hole can get higher-precision results.

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备注/Memo

收稿日期:2020-08-04
基金项目:中国博士后科学基金(2020M681616)
作者简介:杨博(1995—),男,硕士,研究领域为旋转爆震发动机。

更新日期/Last Update: 1900-01-01