<i>Φ</i>3 m高温风洞流场性能校准

唐志共; 陈德江; 朱超; 曾令国; 吴锦水

doi:10.7638/kqdlxxb-2022.0176

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Φ3 m高温风洞流场性能校准

研究论文 | 更新时间：2026-05-28

- Φ3 m高温风洞流场性能校准
- The calibration of of the Φ3 m high temperature tunnel performance
- 空气动力学学报 2023年41卷第11期页码：28-35
- 作者机构：
  
  中国空气动力研究与发展中心超高速空气动力研究所,绵阳,621000
- 作者简介：
  
  唐志共（1965—），男，博士，研究员，研究方向：高速空气动力学研究与应用. E-mail: tangzhigong@cardc.cn
  朱超*（1983—），男，硕士，副研究员，研究方向：高温空气动力试验设备研制及试验技术研究 E-mail:zchf@163.com
- 基金信息：
- DOI：10.7638/kqdlxxb-2022.0176
  中图分类号： V211.74
- 纸质出版：2023
- 稿件说明：
移动端阅览
唐志共, 陈德江, 朱超, 等. Φ3 m高温风洞流场性能校准[J]. 空气动力学学报, 2023, 41(11): 28−35.

TANG Zhigong, CHEN Dejiang, ZHU Chao, et al. The calibration of of the Φ3 m high temperature tunnel performance[J]. 2023, 41(11): 28-35. DOI: 10.7638/kqdlxxb-2022.0176.
唐志共, 陈德江, 朱超, 等. Φ3 m高温风洞流场性能校准[J]. 空气动力学学报, 2023, 41(11): 28−35. DOI： 10.7638/kqdlxxb-2022.0176

TANG Zhigong, CHEN Dejiang, ZHU Chao, et al. The calibration of of the Φ3 m high temperature tunnel performance[J]. 2023, 41(11): 28-35. DOI: 10.7638/kqdlxxb-2022.0176. DOI：

摘要

中国空气动力研究与发展中心

3 m高温风洞是新建成的3米量级暂冲型、自由射流式高温风洞，采用空气/液氧/异丁烷三组元燃烧加热产生高压高温高速气体和真空抽吸联合运行。为评估该高温风洞流场性能，开展了风洞调试和流场校测试验。试验结果表明：风洞可模拟马赫数4～7、高度17～30 km飞行条件下的马赫数、动压、总焓、氧组分、时间等参数，最高总温2335 K；风洞流场品质好、均匀区尺寸大，喷管出口均匀区尺寸达到喷管出口直径的80%以上，均匀区内马赫数和总温偏差均优于2%；流向马赫数菱形均匀区大于理论预测值，流向总温均匀区呈直筒形分布；风洞长时间运行时流场参数波动小，马赫数和总温波动均优于2%。风洞具备了开展高速飞行器空气动力学、推进、材料与结构等试验研究的能力。

Abstract

The

3 m high temperature wind tunnel of China Aerodynamics Research and Development Center is a 3-meter-scale free-jet wind tunnel built recently in China

which is used to conduct aero-thermal loads

aero-thermo-structures

high-enthalpy aerodynamics research and air-breathing propulsion systems testing at different total enthalpy conditions which are conformed to the realistic flight environment. The high-enthalpy flow is produced by burning isobutene

liquid oxygen and air in the combustor

and then goes through the expansion section of nozzle

passes the test section in which the flow is uniform. In the downstream of test section

the flow is exhausted by the diffuser a

nd then arrives at vacuum tank. In order to evaluate the wind tunnel performance

a series of flow field calibration tests were conducted within Mach numbers 4～7. The results indicate that the diameter of uniform flow area is more than 80% of nozzle outlet diameter. In the test section in which the flow is uniform

the deviation of the Mach number and total temperature of flow are within two percent of the average Mach number and total temperature respectively. The tunnel has the ability to simulate Mach number

dynamic pressure

total enthalpy

oxygen components and flight time at Mach numbers of 4～7 and altitudes of 17～30 kilometers. The highest total temperature of flow is 2335 K. The flow field is very stable during long-time operation. The maximum fluctuation of Mach number and total temperature is no more than 2%. The HHT will carry out aerodynamic

propulsion

materials and structures evaluation tests of hypersonic aircraft in the future.

关键词

Keywords

references

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Φ3 m高温风洞流场性能校准

The calibration of of the Φ3 m high temperature tunnel performance

DOI：10.7638/kqdlxxb-2022.0176

摘要

Abstract

关键词

Keywords

references