风洞背景压力对声爆测量影响及抑制技术研究

杨洋; 钱丰学; 周波; 豆帅威; 高荣钊

doi:10.7638/kqdlxxb-2025.0088

欢迎来到能源电力期刊网！

English Version 期刊登录

您当前的位置：

首页 >

文章列表页 >

风洞背景压力对声爆测量影响及抑制技术研究

研究论文 | 更新时间：2026-10-14

- 风洞背景压力对声爆测量影响及抑制技术研究
- Research on the influence of wind tunnel background pressure interference effects on sonic boom measurement and its suppression techniques
- 空气动力学学报 2026年44卷第8期页码：46-57
- 作者机构：
  
  中国空气动力研究与发展中心高速空气动力研究所,绵阳,621000
- 作者简介：
  
  钱丰学*，研究员，研究方向：试验空气动力学. E-mail：qianfengxueml@163.com
- 基金信息：
  
  国家级项目
- DOI：10.7638/kqdlxxb-2025.0088
  中图分类号： V211.7
- 纸质出版：2026
- 稿件说明：
移动端阅览
杨洋, 钱丰学, 周波, 等. 风洞背景压力对声爆测量影响及抑制技术研究[J]. 空气动力学学报, 2026, 44(8): 46−57.

Yang Yang, Qian Fengxue, Zhou Bo, et al. Research on the influence of wind tunnel background pressure interference effects on sonic boom measurement and its suppression techniques[J]. 2026, 44(8): 46-57.
杨洋, 钱丰学, 周波, 等. 风洞背景压力对声爆测量影响及抑制技术研究[J]. 空气动力学学报, 2026, 44(8): 46−57. DOI： 10.7638/kqdlxxb-2025.0088

Yang Yang, Qian Fengxue, Zhou Bo, et al. Research on the influence of wind tunnel background pressure interference effects on sonic boom measurement and its suppression techniques[J]. 2026, 44(8): 46-57. DOI： 10.7638/kqdlxxb-2025.0088.

摘要

风洞试验是评估超声速民机低声爆特性及其设计预测方法的关键手段，而研究风洞背景压力（wind tunnel background pressure

WBP）对声爆测量的影响及其抑制技术对于建立可靠的声爆测量风洞试验技术至关重要。本研究针对风洞背景压力独特的时空分布及耦合特性，结合理论分析与试验验证，探究了其对声爆测量的影响机理，揭示了近似解耦条件下风洞背景压力时域和空间域分布对声爆测量的独立影响机制。提出了一种用于时域影响抑制的基于前馈加PID反馈复合控制方法的前室总压精控策略，使风洞总压控制精度由0.2%～0.3%提升至0.15%以上，显著降低了风洞背景压力的时间不均匀性。通过融合特定试验方案，选取波动最小区域作为测试区，并采用空间平均数据处理方法，形成了一种综合策略，有效增强了高空间扰动环境中对弱声爆信号的分辨与提取能力。最后，将该方法应用于2 m超声速风洞低声爆超声速民机标模测试中，结果表明，其近场声爆测量结果与国际上同尺寸量级连续式风洞所得结果呈现良好一致性，头部激波峰值偏差量小于3%，验证了该框架在抑制风洞背景压力对声爆测量影响方面的有效性。

Abstract

Wind tunnel test is a crucial means for evaluating the low sonic boom characteristics of supersonic civil aircraft and validating related design prediction methods. Investigating the influence of wind tunnel background pressure (WBP) on sonic boom measurement and developing suppression techniques are essential for establishing reliable wind tunnel test methodologies for sonic boom measurement. This study focuses on the unique spatiotemporal distribution and coupling characteristics of WBP. Through theoretical analysis and experimental verification

the mechanism of its influence on sonic boom measurement is explored. The independent effects of WBP distribution in the time and spatial domains under approximate decoupling conditions are successfully revealed. A fine-control strategy for the settling chamber total pressure is proposed

which employs a composite control method combining feedforward and PID feedback to suppress temporal influences. This strategy improves the total pressure control accuracy from 0.2%～0.3% to better than 0.15%

significantly reducing the temporal non-uniformity of WBP. By integrating specific test arrangements

selecting the region with minimal fluctuations as the test section and applying spatial averaging data processing

a comprehensive strategy is formed. This effectively enhances the ability to distinguish and extract weak sonic boom signals in environments with high spatial disturbances. Applying this methodology to low sonic boom supersonic civil aircraft benchmark model tests in a 2 m supersonic wind tunnel shows that the near-field sonic boom measurement results are in good agreement with those obtained from continuous wind tunnels of similar scale internationally. The deviation of the head shock peak is less than 3%

validating the effectiveness of the proposed framework in mitigating the influence of wind tunnel background pressure on sonic boom measurement.

关键词

Keywords

references

Leatherwood J D, Sullivan B M, Shepherd K P, et al. Summary of recent NASA studies of human response to sonic booms[J]. The Journal of the Acoustical Society of America, 2002, 111(1 Pt 2): 586−598. doi: 10.1121/1.1371767

Leng Yan, Zhang JinBai, Qian Zhansen. Superboom prediction for vehicles at supersonic maneuvering flight[J]. Acta Aerodynamica Sinica, 2023, 41(6): 45−54(in Chinese). doi: 10.7638/kqdlxxb-2022.0080

Chen Shusheng, Gu Yiran, Yang Hua, et al. Sonic boom prediction and uncertainly quantification analysis of a low-boom super-sonic aircraft[J]. Acta Aerodynamica Sinica, 2023, 41(4): 41−51(in Chinese). doi: 10.7638/kqdlxxb-2021.0373

Qu Lixia, Han Shuo, Song Yahui, et al. Flight tests and predictions of sonic boom signature for supersonic aircraft[J]. Acta Aerodynamica Sinica, 2022, 40(4): 69−80(in Chinese). doi: 10.7638/kqdlxxb-2022.0018

Qian Zhansen, Liu Zhongchen, Leng Yan, et al. Flight measurement and numerical simulation of sonic boom signature of OS-X0 experimental aircraft[J]. Acta Aerodynamica Sinica, 2019, 37(4): 675−682(in Chinese). doi: 10.7638/kqdlxxb-2018.0276

Morgenstern J. How to accurately measure low sonic boom or model surface pressure in supersonic wind tunnels[C]// 30th AIAA Applied Aerodynamics Conference, Reston, Virginia: AIAA, 2012. doi: 10.2514/6.2012-3215

Durston D A, Elmiligui A A, Cliff S E, et al. Experimental and computational sonic boom assessment of boeing N+2 low boom models[C]// 32nd AIAA Applied Aerodynamics Conference, Atlanta, GA. Reston, Virginia: AIAA, 2014: 2140. doi: 10.2514/6.2014-2140

Carlson H W. Correlation of sonic-Boom theory with wind-tunnel and flight measurements: NASA-TR-R-213 [R]. NASA, 1964.

Mendoza J P, Hicks R M. Further studies of the extrapolation of near-field overpressure data: NASA-TM-X-2219[R]. NASA, 1971.

Hunton L W, Hicks, R M, Mendoza J P. Some effects of wing planform on sonic boom: NASA-TN-D-7160[R]. NASA, 1973.

Carlson H W, Morris O A. Wind-tunnel sonic-boom testing techniques[J]. Journal of Aircraft, 1967, 4(3): 245−249. doi: 10.2514/3.43827

Carlson H W, Mack R J, Morris O A. A wind-tunnel investigation of the effect of body shape on sonic-boom pressure distributions: NASA-TN-D-3106[R]. NASA, 1965.

Carlson H W, Mack R J. A study of the sonic-boom characteristics of a blunt body at a Mach number of 4.14: NASA-TP-1015[R]. NASA, 1977.

Mack R J, Kuhn N. Determination of extrapolation distance with measured pressure signatures from two low-boom models: NASA/TM-2004-213264[R]. NASA, 2004.

Elmiligui A, Cliff S, Aftosmis M, et al. Sonic boom computations for a Mach 1.6 cruise low boom configuration and comparisons with wind tunnel data [C]// 29th AIAA Applied Aerodynamics Conference, Honolulu, Hawaii. Reston, Virginia: AIAA, 2011: 3496. doi: 10.2514/6.2011-3496

Makino Y, Suzuki K, Noguchi M, et al. Non-axisymmetrical fuselage shape modification for drag reduction of a low sonic-boom airplane[C]// 41st Aerospace Sciences Meeting and Exhibit, Reno, Nevada. Reston, Virginia: AIAA, 2003: 557. doi: 10.2514/6.2003-557

Furukawa T, Makino Y, Noguchi M, et al. Supporting system study of wind-tunnel models for validation of aft-sonic-boom shaping design[C]// 26th AIAA Applied Aerodynamics Conference, Honolulu, Hawaii. Reston, Virginia: AIAA, 2008: 6596. doi: 10.2514/6.2008-6596

Durston D, Cliff S, Wayman T, et al. Near field sonic boom test on two low-boom configurations using multiple measurement techniques at NASA Ames [C]// 29th AIAA Applied Aerodynamics Conference, Honolulu, Hawaii. Reston, Virginia: AIAA, 2011: 3333. doi: 10.2514/6.2011-3333

Cliff S E, Elmiligui A A, Aftosmis M J, et al. Design and evaluation of a pressure rail for sonic boom measurements in wind tunnels[C] // 7th International Conference on Computational Fluid Dynamics(ICCFD7), 2012.

Liu Zhongchen, Qian Zhansen, Leng Yan. Review of recent progress of wind tunnel measurement techniques for off-body sonic boom pressure[J]. Acta Aerodynamica Sinica, 2019, 37(4): 636−645(in Chinese). doi: 10.7638/kqdlxxb-2018.0282

中国人民解放军总装备部军事训练教材编辑工作委员会. 高低速风洞气动与结构设计[M]. 北京: 国防工业出版社, 2003.

Yun Qilin. Experimental aerodynamics[M]. Beijing: National Defense Industry Press, 1991 (in Chinese).

Yang Yang, Qian Fengxue, Zhang Changfeng, et al. Research on wind tunnel test technology of sonic boom measurement based on probe[J]. Journal of Experiments in Fluid Mechanics, 2023, 37(6): 92−100(in Chinese). doi: 10.11729/syltlx20210193

Zou Binbin, Zhou Bo, Xiang Bing, et al. Accurate estimation of air pressure in storage tank based on Kalman filter in supersonic wind tunnel[J]. Automation Instrumentation, 2025(1): 27−29(in Chinese). doi: 10.14016/j.cnki.1001-9227.2025.01.027

Todd M, Leonel S, Raul M, et al. X-59 CFD and wind tunnel data comparisons[C]// AIAA Aviation 2023 Forum, San Diego, CA. Reston, Virginia: AIAA, 2023: 4320. doi: 10.2514/6.2023-4320

Carter M, Elmiligui A, Park M, et al. Experimental and computational study of the X-59 wind tunnel model at Glenn research center 8- by 6- foot supersonic wind tunnel: NASA-TM-20220011496[R]. NASA, 2022.

Liu Zhongchen, Qian Zhansen, Leng Yan, et al. Wind tunnel measurement techniques for sonic boom near-field pressure[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(4): 123596(in Chinese). doi: 10.7527/S1000-6893.2019.23596

浏览量

下载量

CSCD

文章被引用时，请邮件提醒。

提交

工具集

关联资源

跨声速抖振机理与控制研究进展及关键技术

阻力舵机翼颤振特性仿真与风洞试验

典型高速飞行器滚转失稳特性研究

典型山体地形下低矮房屋风荷载受周边建筑群干扰效应研究

民用飞机大展弦比大柔性机翼高速静气动弹性载荷风洞试验