2.4 m跨声速风洞壁板参数对核心流均匀性的影响

doi:10.7527/S1000-6893.2015.0026

流体力学与飞行力学

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

2.4 m跨声速风洞壁板参数对核心流均匀性的影响

刘光远, 王瑞波, 郭秋亭, 魏志, 谢疆宇

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

收稿日期:2014-09-16 修回日期:2015-01-19 出版日期:2015-09-15 发布日期:2015-01-26
通讯作者: 刘光远男, 硕士, 工程师。主要研究方向: 实验空气动力学。 Tel: 0816-2462320 E-mail: liugyu@mail.ustc.edu.cn E-mail:liugyu@mail.ustc.edu.cn
作者简介:王瑞波男, 硕士, 高级工程师。主要研究方向: 高速风洞流场调试技术。 Tel: 0816-2462485 E-mail: wrb1973@163.com

Wall parameters influence on centerline flow uniformity in 2.4 m transonic wind tunnel

LIU Guangyuan, WANG Ruibo, GUO Qiuting, WEI Zhi, XIE Jiangyu

High Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2014-09-16 Revised:2015-01-19 Online:2015-09-15 Published:2015-01-26

摘要/Abstract

摘要：

跨声速风洞试验段壁板参数多,影响规律复杂,获得壁板参数对流场均匀性的影响规律是提高设备调试质量与效率的关键途径。基于2.4 m跨声速风洞多期流场校测试验情况,以马赫数分布标准偏差为指标,汇总分析了大型跨声速风洞试验段壁板结构参数对核心流均匀性的影响规律。结果表明,核心流均匀性对试验段入口处加速区壁板开孔率特别敏感,除保证开孔率分布连续外,还应避免加速区气流的过膨胀效应。在风洞运行范围内,引射缝均发挥降低堵塞干扰的作用。

关键词: 跨声速风洞, 流场调试, 核心流均匀性, 壁板参数, 标准偏差

Abstract:

Wall parameters influence on transonic flow field is complicated due to various parameters of transonic wind tunnel test section walls. One key to improve transonic equipment calibration quality and efficiency is to acquire the effect mechanism of wall parameters of wind tunnel test section on flow field uniformity. Based on 2.4 m transonic wind tunnel multi flow field calibration experiments, wall configuration parameters effect on centerline flow uniformity of large transonic wind tunnel test section is summarized and investigated by Mach number distribution standard deviation. Research results show that the centerline flow uniformity is sensitive to porosity ratio of acceleration region, which should be distributed continuously along flow direction. The overexpansion flow should be avoided in acceleration region in order to minimize the wave strength. The ejector-slot is capable of reducing blockage interference over the entire operating range.

Key words: transonic wind tunnel, flow field calibration, centerline flow uniformity, wall parameters, standard deviation

中图分类号:

V211.7

刘光远, 王瑞波, 郭秋亭, 魏志, 谢疆宇. 2.4 m跨声速风洞壁板参数对核心流均匀性的影响[J]. 航空学报, 2015, 36(9): 2930-2938.

LIU Guangyuan, WANG Ruibo, GUO Qiuting, WEI Zhi, XIE Jiangyu. Wall parameters influence on centerline flow uniformity in 2.4 m transonic wind tunnel[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(9): 2930-2938.

参考文献

[1] Chen D H, Yin L P, Wu W H, et al. The test technique for aircraft with high aspect ratio in the 2.4 meter transonic wind tunnel[J]. Acta Aerodynamica Sinica, 2009, 27(5): 542-546 (in Chinese). 陈德华, 尹陆平, 吴文华, 等. 2.4 m跨声速风洞大展弦比飞机测力试验技术研究[J]. 空气动力学学报, 2009, 27(5): 542-546.
[2] Bope A, Gern K L. High speed wind tunnel testing[M]. Beijing: Science Press, 1983 (in Chinese). 博普, 戈因. 高速风洞试验[M]. 北京: 科学出版社, 1983.
[3] Chan Y Y. Analysis of boundary layers on perforated walls of transonic wind tunnels[J]. Journal of Aircraft, 1981, 18(6): 469-473.
[4] Yang W V. Tran-air simulation of wind tunnel flow field subjected to various porous wall boundary condition settings, AIAA-1996-0556[R]. Reston: AIAA, 1996.
[5] Cong C H, Liu Q, Zhang Z F, et al. Numerical simulation of design of transonic wind tunnel perforated test section[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(6): 1014-1019 (in Chinese). 丛成华, 刘琴, 张志峰, 等. 专用跨声速风洞开孔壁试验段设计数值模拟[J]. 航空学报, 2012, 33(6): 1014-1019.
[6] Benson D B. Boundary conditions for CFD simulations of supersonic boundary-layer flow through discrete holes, AIAA-2000-0888[R]. Reston: AIAA, 2000.
[7] Frink N T. Boundary condition for simulation of flow over porous surfaces[J]. Journal of Aircraft, 2003, 40(4): 692-698.
[8] Reed T D, Pope T C, Cooksey J M. Calibration of transonic and supersonic wind tunnels, NASA-CR-2920[R]. Washington, D.C.: NASA, 1977.
[9] Zheng G F. On the accelerating airflow problem in the test section of a transonic wind tunnel[J]. Journal of Nanjing Aeronautical Institute, 1982, 41(S1): 77-84 (in Chinese). 郑国锋. 跨声速风洞试验段中气流的加速问题[J]. 南京航空学院学报, 1982, 41(S1): 77-84.
[10] Jackson F M. Calibration of the AEDC-PWT 16-ft transonic tunnel at test section wall porosities of two, four, and six percent, AEDC-TM-76-13[R].Tennessee: AEDC,1976.
[11] Elfstrom G M. Optimum porosity for an inclined-hole transonic test section wall treated for edge tone noise reduction, AIAA-1988-2003[R]. Reston: AIAA, 1988.
[12] Marino A, Imperatore B, Ragni A. Streamwise porosity distribution optimization for minimising wall interference in a transonic wind tunnel, AIAA-2009-1485[R]. Reston: AIAA, 2009.
[13] Ching F L. Wind-tunnel wall interference reduction by streamwise porosity distribution[J]. AIAA Journal, 1972,10(4): 547-550.
[14] Allan M R, Badcock K J, Barakos G N, et al. Wind tunnel interference effects on a 70° delta wing[J]. The Aeronautical Journal, 2004, 108(1088): 505-513.
[15] Wang W X. The first term flowfield calibration in 2.4 m transonic wind tunnel, CARDC-2[R]. Mianyang: China Aerodynamics Research and Development Center, 1999 (in Chinese). 王维新. 2.4 m跨声速风洞第一期流场校测, CARDC-2 [R]. 绵阳: 中国空气动力研究与发展中心, 1999.
[16] Wang W X. The Second term flowfield calibration in 2.4 m transonic wind tunnel, CARDC-2[R]. Mianyang: China Aerodynamics Research and Development Center, 1999 (in Chinese). 王维新. 2.4 m跨声速风洞第二期流场校测, CARDC-2[R]. 绵阳: 中国空气动力研究与发展中心, 1999.
[17] Wang W X. The first term flowfield calibration in half model test section of 2.4 m transonic wind tunnel, CARDC-2[R]. Mianyang: China Aerodynamics Research and Development Center, 2003 (in Chinese). 王维新. 2.4 m跨声速风洞半模试验段第一期流场校测, CARDC-2[R]. 绵阳: 中国空气动力研究与发展中心, 2003.
[18] Hua J. Final report of the performance enhancement (flowfield calibration) in half model test section of 2.4 m transonic wind tunnel, CARDC-2[R]. Mianyang: China Aerodynamics Research and Development Center, 2003 (in Chinese). 华杰. 2.4 m跨声速风洞半模试验段性能拓展(流场校测)技术总结报告, CARDC-2[R]. 绵阳: 中国空气动力研究与发展中心, 2003.
[19] Zhong S D. The third term flowfield calibration in full model test section of 2.4 m transonic wind tunnel, CARDC-2[R]. Mianyang: China Aerodynamics Research and Development Center, 2006 (in Chinese). 钟世东. 2.4 m跨声速风洞全模试验段第三期流场校测, CARDC-2 [R]. 绵阳: 中国空气动力研究与发展中心, 2006.
[20] Commission of Science, Technology and Industry for National Defense (COSTIND). Specification for flow quality of high and low speed wind tunnels(GJB1179-91)[S]. Beijing: National Defence Industry Press, 1991 (in Chinese). 国防科学技术工业委员会. 高速风洞和低速风洞流场品质规范(GJB1179-91)[S]. 北京: 国防工业出版社, 1991.
[21] Zeng K C, Xiang J W. Uncertainty analysis of flight dynamic characteristics for hypersonic vehicles[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(4): 798-808 (in Chinese). 曾开春, 向锦武. 高超声速飞行器飞行动力学特性不确定分析[J]. 航空学报, 2013, 34(4): 798-808.
[22] Li J Q, Zhang P, Wang Y Q. Method of uncertainty analysis for wind tunnel test data[J]. Acta Aerodynamica Sinica, 2000, 18(3): 299-306 (in Chinese). 李建强, 张平, 王义庆. 风洞数据不确定度分析方法[J]. 空气动力学学报, 2000, 18(3): 299-306.
[23] Xie J Y, Wu J Q, Zhong S D, et al. Uncertainty analysis for large aircraft test in 2.4 m transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2010, 24(6): 65-68 (in Chinese). 谢疆宇, 吴军强, 钟世东, 等. 2.4 m跨声速风洞大型飞机试验不确定度评估[J]. 实验流体力学, 2010, 24(6): 65-68.
[24] Carol D W, Robert M B. Wall boundary layer measurements for the NASA Langley transonic dynamics tunnel, NASA/TM-2007-214867[R]. Washington, D.C.: NASA,2007.

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

2.4 m跨声速风洞壁板参数对核心流均匀性的影响

Wall parameters influence on centerline flow uniformity in 2.4 m transonic wind tunnel

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 9

编辑推荐

Metrics

本文评价

[1]	朱博, 廖达雄, 陈振华, 陈吉明. 跨声速流场扰动模态与湍流度精细测量[J]. 航空学报, 2023, 44(4): 126378-126378.
[2]	吕治国, 龚红明, 常雨, 廖振洋, 钟涌. 跨越第二宇宙速度的膨胀管风洞研制[J]. 航空学报, 2022, 43(S2): 138-151.
[3]	刘光远, 张林, 陈德华, 林学东, 贾智亮. 跨声速风洞斜孔壁非线性流动试验[J]. 航空学报, 2019, 40(5): 122497-122497.
[4]	崔晓春, 孟凡民, 李庆利, 张刃, 李兴龙. 跨声速风洞调节片式二喉道中心体构型初步研究[J]. 航空学报, 2017, 38(11): 121327-121327.
[5]	鞠炼, 白俊强, 郭斌, 崔晓春, 李兴龙. 槽壁几何参数对跨声速风洞流场品质的影响[J]. 航空学报, 2016, 37(5): 1440-1453.
[6]	赵子杰, 高超, 张正科. 新型人工转捩技术及风洞试验验证[J]. 航空学报, 2015, 36(6): 1830-1838.
[7]	钱卫, 张桂江, 刘钟坤. 飞机全动平尾颤振特性风洞试验[J]. 航空学报, 2015, 36(4): 1093-1102.
[8]	丛成华, 刘琴, 张志峰, 彭强. 专用跨声速风洞开孔壁试验段设计数值模拟[J]. 航空学报, 2012, (6): 1014-1019.
[9]	丛成滑;彭强;王海锋. 槽壁试验段低超声速流场特性数值模拟[J]. 航空学报, 2010, 31(12): 2302-2308.