Measurement of plasma parameters in high-enthalpy arc-heated wind tunnel

ZENG Hui; YAN Xianxiang; CHEN Zhiming; MIAO Wenbo; ZHOU Jingyun

doi:10.7638/kqdlxxb-2025.0114

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Measurement of plasma parameters in high-enthalpy arc-heated wind tunnel

更新时间：2026-05-28

- Measurement of plasma parameters in high-enthalpy arc-heated wind tunnel
- Vol. 43, Issue 7, Pages: 108-117(2025)
- 作者机构：
  
  中国航天空气动力技术研究院电弧等离子应用装备北京市重点实验室,北京,100074
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2025.0114
  CLC： V556.4
- Published：2025
- 稿件说明：
移动端阅览
曾徽, 闫宪翔, 陈智铭, 等. 高焓电弧风洞等离子体参数测量[J]. 空气动力学学报, 2025, 43(7): 108−117.

ZENG Hui, YAN Xianxiang, CHEN Zhiming, et al. Measurement of plasma parameters in high-enthalpy arc-heated wind tunnel[J]. 2025, 43(7): 108-117.
曾徽, 闫宪翔, 陈智铭, 等. 高焓电弧风洞等离子体参数测量[J]. 空气动力学学报, 2025, 43(7): 108−117. DOI： 10.7638/kqdlxxb-2025.0114

ZENG Hui, YAN Xianxiang, CHEN Zhiming, et al. Measurement of plasma parameters in high-enthalpy arc-heated wind tunnel[J]. 2025, 43(7): 108-117. DOI： 10.7638/kqdlxxb-2025.0114.

摘要

地面试验是开展等离子体流场特性表征的重要手段，针对高焓流场等离子体参数辨识的需求，在电弧风洞开展了典型流场等离子体参数测量研究。利用带攻角钝楔平板模型模拟飞行器大面积区域流场，采用静电探针诊断技术，结合电动扫描技术进行了钝楔模型流场电子密度的空间分布测量，同时使用数值方法开展了对应状态的仿真模拟，并对两者进行了对比验证。研究发现：对于当前风洞条件，矩形喷管

向80 mm厚度核心区的等离子体参数基本保持均匀稳定，在靠近喷管壁面的两侧边缘位置受边界层影响电子密度明显衰减。本文所采用的探针测量方案对于电子密度测试的影响较小：相对高电子密度（10

–3

）工况电子密度实测值与计算值吻合良好，偏差小于0.5个数量级；低电子密度（10

–3

）工况等离子体电子密度实测值显著高于计算值，偏差在0.5～1个量级，初步分析认为电极烧蚀带来的铜污染效应是重要影响因素。本研究为飞行器近壁面等离子体参数测量提供了有效验证手段。

Abstract

Ground-based testing represents a critical method for plasma flow field characterization. To address the requirements for plasma parameter identification in high-enthalpy flows

this study performed experimental measurements of typical plasma parameters in an arc-heated wind tunnel. A blunt wedge flat-plate model with angle of attack was used to simulate spacecraft flow fields over large surface areas. The spatial distribution of electron density in the wedge model flow field was measured using electrostatic probe diagno

stics combined with motorized scanning technology

while corresponding numerical simulations were conducted for comparison and validation. The investigation revealed that under current wind tunnel conditions

plasma parameters remained essentially uniform and stable within the 80 mm thick core region along the

-direction of the rectangular nozzle. However

electron density showed significant attenuation near the nozzle sidewalls due to boundary layer effects. The employed probe measurement scheme demonstrated minimal influence on electron density detection. For relatively high electron density conditions (～10

–

)

measured values agreed well with simulations

showing deviations less than 0.5 orders of magnitude. In contrast

under low electron density conditions (～10

–

)

measured values significantly exceeded computational results by 0.5–1 orders of magnitude. Preliminary analysis indicated that copper contamination from electrode ablation served as a major contributing factor for this discrepancy. This study provides an effective validation method for near-wall plasma parameter measurements in aircraft applications.

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references

DIRSA E. The telemetry and communication problem of re-entrant space vehicles[J]. Proceedings of the IRE, 1960, 48(4): 703−713. doi: 10.1109/jrproc.1960.287451

HUBER P W, SIMS T. Research approaches to the problem of reentry communications blackout: NASA-TM-X-56839[R]. NASA, 1965.

AKEY N D, CROSS A E. Radio blackout alleviation and plasma diagnostic results from a 25, 000 foot per second blunt-body reentry: NASA-TN-D-5615[R]. NASA, 1970.

KANG S W, JONES W L, DUNN M G. Theoretical and measured electron-density distributions at high altitudes[J]. AIAA Journal, 1973, 11(2): 141−149. doi: 10.2514/3.50446

LU F K, MARREN D E. Advanced hypersonic test facilities[M]. AIAA, 2002. doi: 10.2514/4.866678

WANG Q, HUANG J D, NIE C S, et al. Research on electron density measurements for high enthalpy flows[J]. Scientia Sinica (Technologica), 2016, 46(5): 500−508(in Chinese). doi: 10.1360/N092015-00295

YU H R. Oxyhydrogen combustion and detonation driven shock tube[J]. Acta Mechanica Sinica, 1999, 15(2): 97−107. doi: 10.1007/BF02485874

HOLDEN M S, PARKER R A. LENS hypervelocity tunnels and application to vehicle testing at duplicated flight conditions[M]//Advanced Hypersonic Test Facilities. Reston, VA: AIAA, 2002: 73−110. doi: 10.2514/5.9781600866678.0073.0110

ERDOS J, CALLEJA J, TAMAGNO J. Increase in the hypervelocity test envelope of the HYPULSE shock-expansion tube[C]// 25th Plasmadynamics and Lasers Conference, Colorado Springs, CO, USA. AIAA, 1994: AIAA 1994−2524. doi: 10.2514/6.1994-2524

STEWART D, GOKCEN T, CHEN Y K. Characterization of hypersonic flows in the AHF and IHF of NASA Ames arc-jet facilities[C]// 41st AIAA Thermophysics Conference, San Antonio, Texas. AIAA, 2009: AIAA 2009-4237. doi: 10.2514/6.2009-4237

CHEN L Z, OU D B, GAO H. Aerodynamic heating technology of thermal protection sytem in the arc-heated wind tunnel for hypersonic aircraft [M]. Beijing: Science Press, 2020(in Chinese).

BOTTIN B, CHAZOT O, CARBONARO M, et al. The VKI plasmatron characteristics and performance: ADP010745[R]. Defense Technical Information Center, 2000.

MACDERMOTT W, HORN D, FISHER C. Flow contamination and flow quality in arc heaters used for hypersonic testing[C]// 17th Aerospace Ground Testing Conference, Nashville, TN, USA. AIAA, 1992: AIAA 1992−4028. doi: 10.2514/6.1992-4028

ZENG H, CHEN Z M, YAN X X, et al. Quantitative measurements of copper contamination in arc heater by using emission spectroscopy[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(4): 123521 (in Chinese).

STEFFENS L, KOCH U, ESSER B, et al. Characterization of weakly ionized argon flows for radio blackout mitigation experiments[J]// Progress in Flight Physics, 2017, 9: 335−348. doi: 10.1051/eucass/2016090335

ZHUKOV A A. Plasma diagnostics[M]. Cambridge International Science Publishing, 2000.

CONDE L. An introduction to Langmuir probe diagnostics of plasmas[D]. Madrid: Universidad Politécnica de Madrid, 2011.

LIM H B, HOUK R S. Langmuir probe measurement of electron temperature in a supersonic jet extracted from an inductively coupled plasma[J]. Spectrochimica Acta Part B: Atomic Spectroscopy, 1990, 45(4-5): 453−461. doi: 10.1016/0584-8547(90)80121-X

SHUN'KO E V. Langmuir probe in theory and practice[M]. Florida: Universal-Publishers, 2009.

BOSE S, KAUR M, CHATTOPADHYAY P K, et al. Langmuir probe in collisionless and collisional plasma including dustyplasma[J]. Journal of Plasma Physics, 2017, 83(2): 615830201. doi: 10.1017/s0022377817000289

KEIDAR M, KIM M, BOYD I D. Electromagnetic reduction of plasma density during atmospheric reentry and hypersonic flights[J]. Journal of Spacecraft and Rockets, 2008, 45(3): 445−453. doi: 10.2514/1.32147

NIKIFOROV A Y, LEYS C, GONZALEZ M A, et al. Electron density measurement in atmospheric pressure plasma jets: Stark broadening of hydrogenated and non-hydrogenated lines[J]. Plasma Sources Science and Technology, 2015, 24(3): 034001. doi: 10.1088/0963-0252/24/3/034001

CHEN F F. Introduction to plasma physics[M]. Springer Science Business Media, 2012.

CHEN F F. Langmuir probes in RF plasma: Surprising validity of OML theory[J]. Plasma Sources Science and Technology, 2009, 18(3): 035012. doi: 10.1088/0963-0252/18/3/035012

EVANS J S, HUBER P W, SCBEXNAYDER C J. Calculation of electron concentration for a blunt body at orbital speed and comparison with experimental data: NASA-TN-D-6294[R]. NASA, 1971.

MIAO W B, HUANG F, CHENG X L, et al. Plasma prediction of reentry vehicle and gas components[J]. Chinese Journal of Computational Physics, 2015, 32(1): 27−32(in Chinese). doi: 10.3969/j.issn.1001-246X.2015.01.005

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