Uncertainty analysis in scramjet performance parameters measurements

LIAO Wenhao; GUO Jinxin; LIU Xiaoyong

doi:10.13224/j.cnki.jasp.2020.11.019

Chinese

您当前的位置：

首页 >

文章列表页 >

Uncertainty analysis in scramjet performance parameters measurements

更新时间：2026-07-07

- Uncertainty analysis in scramjet performance parameters measurements
- Vol. 35, Issue 11, Pages: 2421-2428(2020)
- 作者机构：
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2020.11.019
  CLC：
- Published：2020
- 稿件说明：
移动端阅览
廖文豪, 郭金鑫, 刘小勇. 超燃冲压发动机性能参数测量不确定度分析[J]. 航空动力学报, 2020, 35(11): 2421-2428.

doi: 10.13224/j.cnki.jasp.2020.11.019
廖文豪, 郭金鑫, 刘小勇. 超燃冲压发动机性能参数测量不确定度分析[J]. 航空动力学报, 2020, 35(11): 2421-2428. DOI： 10.13224/j.cnki.jasp.2020.11.019.

doi: 10.13224/j.cnki.jasp.2020.11.019 DOI：

摘要

以AIAA(AIAA S-071A-1999)推荐的不确定度评估标准

借鉴国内外在风洞试验、航空发动机性能测量、火箭发动机地面试验性能等不确定度分析方面开展的研究工作

建立了符合统计学一般原理的超燃冲压发动机总体性能参数测量不确定度分析和计算方法

开展了超燃冲压发动机总体性能参数测量不确定度进行了分析。结果表明:超燃冲压发动机自由射流试验中系统误差引入的不确定度占主导地位

占总不确定度的90%以上。该研究结果有利于提高超燃冲压发动机总体性能测量精度

为超燃冲压发动机的科学研究和工程设计提供支撑。

Abstract

Based on wind tunnel test uncertainty assessment of AIAA S-071A-1999 and the uncertainty study for the wind tunnel testing

aeroengine performance testing and rocket ground testing in the international space power community

an uncertainty analysis method for the scramjet performance testing was established

and corresponding analysis was given.Results showed that the uncertainty induced by the free-jet testing measurement was predominant in evaluating the overall scramjet performance

and the bias limit was over 90% in the uncertainty of scramjet performance parameters measurements.In conclusion

some valuable results and suggestions about the uncertainty of overall performance of scramjet were obtained

and these results can improve the accuracy in scramjet performance parameters measurements

showing prominent application prospect in scramjet development.

关键词

Keywords

references

Views

201

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Effect of inlet internal contraction ratio on performance of solid fuel scramjet

Channel layout and shape optimization of active cooling thin⁃walled structures

Flow channel scheme of U⁃shaped cooling channel in scramjet

Fuel/air mixing characteristics of scramjet combustor based on acetone⁃PLIF technology

Aero-engine cycle design approach for multiple operating conditions performance reliability

Related Author

LI Biao

WEI Zhi-jun

CHI Hong-wei

WANG Ning-fei

Shiping SUN

Dehui XU

Daohuang LIU

Zheng HU

Related Institution

School of Aerospace Engineering, Beijing Institute of Technology

School of Aeronautical Manufacturing Engineering， Nanchang Hangkong University

Faculty of Rocket and Space Technology， National Aerospace University “KhAI”

College of Aerospace Science and Engineering，National University of Defense Technology

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

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