Development of hot-wire probe calibration wind tunnel based on compressible fluid
-
摘要: 在可压缩流体中利用热线技术进行湍流度测量时，其输出不仅与脉动速度有关，也和流体温度、密度紧密相关。因此，需要建立与高速可压缩流体特征相似的校准装置，在使用前对热线探针进行准确校准。基于亚跨声速可压缩流体，对热线探针校准风洞的气动总体方案、关键结构设计、测控处系统研制等做了介绍和说明。风洞流场校测结果表明，模型区Ma最大偏差0.002，风洞速压可以降低至常规速压的50%以下，也可增至常规速压的1.7倍以上，温度和密度调节范围宽，流场均匀性好，满足热线探针校准需求。Abstract: The output of the hot-wire is related not only to the fluctuation velocity, but also to the fluid temperature and density when the hot-wire technology is used to measure the turbulence intensity in a compressible fluid. Therefore, it is necessary to establish a calibration facility with similar characteristics to a high speed compressible fluid so that the accurate calibration of the hot-wire probe can be done before its usage. In this paper, the aerodynamic overall scheme, structural design and development of measurement and control system of the hot-wire probe calibration wind tunnel are introduced and illustrated based on subsonic and transonic compressible fluids. According to the results of the wind tunnel flow field calibration tests, the maximum deviation of the Mach number in the model area is 0.002; the dynamic pressure can be adjusted from 0.5 to 1.7 times of the normal dynamic pressure; the variation range of temperature and density is wide; the uniformity of the flow field are good. All the requirements for the hot-wire probe calibration are satisfied.
-
Key words:
- compressible fluid /
- hot-wire probe /
- calibration wind tunnel /
- flow field calibration
-
图 2 收缩段和亚声速喷管流线图(Ma=0.8)
Figure 2. Streamlines pattern of contraction section and subsonic nozzle(Ma=0.8)
图 3 亚声速喷管出口速度分布(Ma=0.8)
Figure 3. Velocity distribution of subsonic nozzle outlet (Ma=0.8)
图 4 收缩段至亚扩段流场马赫数总体分布(Ma=0.8)
Figure 4. Flow Mach number population distribution from contraction section to sub segment(Ma=0.8)
图 10 热线探针校准风洞测控处系统原理框图
Figure 10. Scheme of measurement,control and processing system of hot-wire calibration wind tunnel
图 12 总温排管测温点分布示意图
Figure 12. Scheme of measuring temperature point distribution on the total temperature exhaust pipe
图 13 无加热常规速压条件下流校结果
Figure 13. Flow calibration result under conventional dynamic pressure condition without heating
表 1 典型马赫数下的温度测量结果
Table 1. The result of temperature measurement under topic Mach numbers conditions
Ma T0/℃ 中心流场T/℃ ΔT/℃ 0.30 23.75 23.58 -0.17 0.35 23.30 23.19 -0.11 0.40 23.00 22.85 -0.15 0.45 22.77 22.53 -0.24 0.50 22.49 22.19 -0.30 0.55 22.28 21.99 -0.29 0.60 22.10 21.72 -0.38 0.65 21.93 21.55 -0.38 0.70 21.79 21.35 -0.44 0.75 21.71 21.22 -0.49 0.80 21.67 21.24 -0.43 0.85 21.63 21.11 -0.52 0.90 21.59 21.10 -0.49 0.95 21.52 21.25 -0.27 
下载: 导出CSV
-
[1] 朱博, 汤更生. 声学风洞流场低湍流度及频谱测量研究[J]. 实验流体力学, 2015, 29 (4): 58-64. http://www.syltlx.com/CN/abstract/abstract10860.shtmlZhu B, Tang G S. Low turbulence intensity and spectrum measurement research in aeroacoustic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2015, 29 (4):58-64. http://www.syltlx.com/CN/abstract/abstract10860.shtml [2] 贾青, 杨志刚, 李启良. 汽车风洞试验段流场的试验研究[J]. 实验流体力学, 2011, 25 (6): 33-37. http://www.syltlx.com/CN/abstract/abstract10595.shtmlJia Q, Yang Z G, Li Q L. Test research of the flow filed inside the test section of the automative wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2011, 25 (6): 33-37. http://www.syltlx.com/CN/abstract/abstract10595.shtml [3] 田于逵, 江宏. 利用热线风速仪在风洞中研究舰艇尾部流动特性[J]. 船舶力学, 1998, 2 (2): 13-21. http://www.cnki.com.cn/Article/CJFDTOTAL-CBLX199802002.htmTian Y K, Jiang H. Study on the wake characteristics naval vessels using a hot-wire anemometer in a wind tunnel[J]. Ship Mechanics, 1998, 2 (2): 13-21. http://www.cnki.com.cn/Article/CJFDTOTAL-CBLX199802002.htm [4] 高丽敏, 席光, 王尚锦, 等. 用热线风速仪测量叶轮后叶片扩压器流场[J]. 工程热物理学报, 2005, 26 (4): 559-601. http://www.cnki.com.cn/Article/CJFDTOTAL-GCRB200504018.htmGao L M, Xi G, Wang S J, et al. Experiment investigation on a vaned diffuser flow filed behind a centrifugal impeller using constant temperature anemometer[J]. Journal of Engineering Thermophysics, 2005, 26 (4): 559-601. http://www.cnki.com.cn/Article/CJFDTOTAL-GCRB200504018.htm [5] De Souza F, Tavoularis S. Hot-wire response in high-subsonic flow[R]. AIAA-99-0310, 1999. [6] Jones G S. Wind tunnel requirements for hot-wire calibration (Invited) [R]. AIAA-94-2534, 1994. [7] Amber L Favaregh. A new approach for calibration of hot-wires for use in uncertain environments[R]. AIAA-2006-2809, 2006. [8] Zinoviev V, Lebiga V, Chung K M, et al. Application of hot-wire technology in a slowdown type transonic wind tunnel[R]. AIAA-2001-0308, 2001. [9] Nagabushana K A, Stainback P C. A rational technique for calibrating hot-wire probe in subsonic to supersonic speed[R]. AIAA-94-2536, 1994. [10] Stainback P C. Some influences of approximate values for velocity, density, and toal temperature sensitivities on hot-wire anemometer results[R]. AIAA-86-0506, 1986. [11] 刘政崇. 高低速风洞气动与结构设计[M]. 北京: 国防工业出版社, 2003. [12] 中国人民解放军总装备部. GJB 1179A-2012高速风洞和低速风洞流场品质要求[S]. 北京: 总装备部军标出版发行部, 2013. -
点击查看大图
计量
- 文章访问数: 521
- HTML全文浏览量: 127
- PDF下载量: 25
- 被引次数: 0
