Application of center-line probe in transonic wind tunnel

吴盛豪; 裴海涛; 陈吉明; 陈钦

doi:10.13224/j.cnki.jasp.2018.10.017

Chinese

您当前的位置：

首页 >

文章列表页 >

Application of center-line probe in transonic wind tunnel

更新时间：2026-07-07

- Application of center-line probe in transonic wind tunnel
- Vol. 33, Issue 10, Pages: 2451-2457(2018)
- 作者机构：
  
  1. 中国空气动力研究与发展中心空气动力学国家重点实验室,四川,绵阳,621000
  2. 中国空气动力研究与发展中心设备设计与测试技术研究所,四川,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2018.10.017
  CLC：
- Published：2018
- 稿件说明：
移动端阅览
吴盛豪, 裴海涛, 陈吉明, 陈钦. 跨声速风洞中轴探管的应用[J]. 航空动力学报, 2018, 33(10): 2451-2457.

doi: 10.13224/j.cnki.jasp.2018.10.017
吴盛豪, 裴海涛, 陈吉明, 陈钦. 跨声速风洞中轴探管的应用[J]. 航空动力学报, 2018, 33(10): 2451-2457. DOI： 10.13224/j.cnki.jasp.2018.10.017.

doi: 10.13224/j.cnki.jasp.2018.10.017 DOI：

摘要

以气动中心0.6m×0.6m连续式跨超声速风洞为试验平台

开展了轴探管不同开孔型式、不同长度及不同安装方位对测试结果的影响研究。测试结果表明:对称开孔型式轴探管测量结果普遍优于交错开孔型式；当试验马赫数小于1.0时

短轴探管测试结果与长轴探管相当

但当试验马赫数不小于1.0时

短轴探管头锥对测试结果影响较大；当试验马赫数小于1.0时

轴探管测孔加工质量的一致性对测试结果有显著影响。

Abstract

In the 0.6m×0.6m continuous transonic wind tunnel of CARDC

experiments for center-line probes with different arrangements of orifices

different length and different installation sites were conducted. Results indicated that

the Mach number fluctuation tested with the center-line probe of symmetry orifices was weaker than that of staggered orifices. And when the experiment Mach number was below 1.0

the experiment result of short center-line probe agreed well with the long probe. But when the experiment Mach number was higher than 1.0

the Mach number fluctuated severely due to the nose cone of the short probe. And when the experiment Mach number was below 1.0

the machining quality of orifices along the center-line probe had a great influence on the test results.

关键词

Keywords

references

Views

518

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Design and test of short centerline probe in continuous transonic wind tunnel

Noise reduction technology in test section of continuous transonic wind tunnel

Variable angle of attack start experiment of 2D curved compression inlet

Application research on supersonic nozzle performance optimization

Scramjet nozzle with adjustable cowl scheme

Related Author

Haijun DENG

Bo XIONG

Xinfu LUO

Shaozun HONG

Tengji LI

Libo ZHANG

Xinfeng HAN

Jinlei LÜ

Related Institution

High Speed Aerodynamics Institute，China Aerodynamics Research and Development Center

Key Laboratory of Unsteady Aerodynamics and Flow Control of Ministry of Industry and Information Technology，College of Aerospace Engineering， Nanjing University of Aeronautics and Astronautics

Facilitiy Design and Instrumentation Institute， China Aerodynamics Research and Development Center

海交通大学船舶海洋与建筑工程学院

上海交通大学船舶海洋与建筑工程学院

AI问答

Postal code：100079
Tel：（010）53879206 Email：tmw@bjxintong.com.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备09082226号-64 京公网安备11010602201714号
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰