Numerical simulation and experimental test of unsteady flow field for oscillating vanes gust generator in high-speed wind tunnel

ZHANG Ying; LIU Nan

doi:10.11729/syltlx20210093

Volume 36 Issue 5

Sep. 2022

Turn off MathJax

Article Contents

Abstract

References

Journal of Experiments in Fluid Mechanics > 2022 > 36(5): 83-89. > DOI: 10.11729/syltlx20210093

ZHANG Y，LIU N. Numerical simulation and experimental test of unsteady flow field for oscillating vanes gust generator in high-speed wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2022，36（5）：83-89.. DOI: 10.11729/syltlx20210093

Citation:

PDF (6959 KB)

Numerical simulation and experimental test of unsteady flow field for oscillating vanes gust generator in high-speed wind tunnel

ZHANG Ying^,,
LIU Nan

Aeronautical Science and Technology Key Lab for High Speed and High Reynolds Number Aerodynamic Force Research, AVIC Aerodynamics Research Institute, Shenyang　110034, China

More Information

Received Date: August 15, 2021
Revised Date: January 04, 2022
Accepted Date: January 23, 2022

Graphical Abstract

Abstract

Abstract

Gust generator is the important equipment of the gust test system. In order to reduce the risk of development, a set of oscillating vanes gust generator suitable for 0.6 m continuous transonic wind tunnel was designed and processed. The self-developed ENSMB software was used to numerically simulate the unsteady flow field for the generator, and the formation mechanism and distribution characteristic of the disturbance velocity field downstream of the generator were analyzed. The research focused on the influence of the oscillating frequency and maximum oscillating amplitude of gust vanes on the gust velocity amplitude, and compared the results with the experimental data. The results show that the calculated results are in good agreement with that obtained by experiment. The gust velocity field downstream is caused by the vortex shedding from the vane, and changes periodically and sinusoidally with time. The gust velocity amplitude increases first with the increase of the maximum oscillating amplitude of gust vanes. When the maximum oscillating amplitude is 10°, the gust velocity amplitude reaches the maximum, and then there is no obvious change. This is probably due to the stall caused by the maximum oscillating amplitude increase. The frequency change only affects the frequency of the gust velocity, but has no obvious influence on the gust velocity amplitude.
- oscillating vanes gust generator,
- gust velocity field,
- oscillating frequency,
- maximum oscillating amplitude,
- unsteady

FullText(HTML)

References (16)

References

[1]	赵卓林,陈同银,唐超,等. 大展弦比飞机阵风降载策略与载荷测试分析[J]. 飞机设计,2018,38(5):17-20. ZHAO Z L,CHEN T Y,TANG C,et al. The gust load alleviation design and flight tests for an aircraft with large aspect ratio[J]. Aircraft Design,2018,38(5):17-20.
[2]	刘澄澄,赵永辉. 弹性飞机阵风减缓研究[J]. 航空计算技术,2014,44(1):78-82. DOI: 10.3969/j.issn.1671-654X.2014.01.020 LIU C C,ZHAO Y H. Research on gust response alleviation of an elastic aircraft[J]. Aeronautical Computing Technique,2014,44(1):78-82. doi: 10.3969/j.issn.1671-654X.2014.01.020
[3]	刘澄澄. 柔性飞机突风响应与载荷减缓研究[D]. 南京: 南京航空航天大学, 2014. LIU C C. Research on gust response analysis and alleviation of the flexible aircraft[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2014.
[4]	ALLEN N J, QUINN M. Development of a transonic gust rig for simulation of vertical gusts on half-models[C]//Proc of the 31st AIAA Aerodynamic Measurement Technology and Ground Testing Conference. 2015. doi: 10.2514/6.2015-2403
[5]	REDD L, HANSON P, WYNNE E C. Evaluation of a wind-tunnel gust response technique including correlations with analytical and flight test results[R]. NASA TP 1501 c.1, 1979.
[6]	SCOTT R, VETTER T, PENNING K, et al. Aeroservoe-lastic testing of a sidewall mounted free flying wind-tunnel model[C]//Proc of the 26th AIAA Applied Aerodynamics Conference. 2008. doi: 10.2514/6.2008-7186
[7]	SILVA W, VARTIO E, SHIMKO A, et al. Development of aeroservoelastic analytical models and gust load alleviation control laws of a SensorCraft wind-tunnel model using measured data[C]//Proc of the 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. 2006. doi: 10.2514/6.2006-1935
[8]	BARTELS R E, CHWALOWSKI P. Computational fluid dynamics simulations of the transonic dynamics tunnel airstream oscillators[C]//Proc of the AIAA Scitech 2021 Forum. 2021. doi: 10.2514/6.2021-0835
[9]	SILVA W, PERRY B, FLORANCE J, et al. An overview of the semi-span super-sonic transport （S4T） wind-tunnel model program[C]//Proc of the 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. 2012. doi: 10.2514/6.2012-1552
[10]	CHRISTHILF D, MOULIN B, RITZ E, et al. Characteristics of control laws tested on the semi-span super-sonic transport（S4T）wind-tunnel model[C]//Proc of the 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. 2012. doi: 10.2514/6.2012-1555
[11]	梁鉴,唐建平,杨远志,等. FL-12风洞突风试验装置研制[J]. 实验流体力学,2012,26(3):95-100. DOI: 10.3969/j.issn.1672-9897.2012.03.018 LIANG J,TANG J P,YANG Y Z,et al. The development of gust generators in FL-12 wind tunnel[J]. Journal of Experiments in Fluid Mechanics,2012,26(3):95-100. doi: 10.3969/j.issn.1672-9897.2012.03.018
[12]	金华,王辉,张海酉,等. FL-13风洞突风发生装置研究[J]. 空气动力学学报,2016,34(1):40-46. DOI: 10.7638/kqdlxxb-2015.0134 JIN H,WANG H,ZHANG H Y,et al. Investigation on gust response test apparatus in FL-13 wind tunnel[J]. Acta Aerodynamica Sinica,2016,34(1):40-46. doi: 10.7638/kqdlxxb-2015.0134
[13]	楚龙飞, 刘晓燕, 吴志刚. 阵风减缓模型风洞试验的阵风发生器设计与应用[C]//第十一届全国空气弹性学术交流会议论文集. 2009.
[14]	陈磊,吴志刚,杨超,等. 弹性机翼阵风响应和载荷减缓与风洞试验验证[J]. 工程力学,2011,28(6):212-218. CHEN L,WU Z G,YANG C,et al. Gust response, load alleviation and wind-tunnel experiment verification of elastic wing[J]. Engineering Mechanics,2011,28(6):212-218.
[15]	王娜, 李艳亮, 董军. 航空数值计算平台ENSMB简介[C]//中国力学学会学术大会论文集. 2009.
[16]	王娜,张铁军,董军. 多重网格技术在民机模型流场数值模拟中的应用[J]. 气动研究与实验,2009,27(2):5-8. WANG N,ZHANG T J,DONG J. Research on application of multi-grid technology in numerical simulation of viscous flow field of civil aircraft[J]. Aerodynamic Research & Experiment,2009,27(2):5-8.

Cited By

Get Citation

PDF

XML

Article Metrics

Article views (281) PDF downloads (36)

Numerical simulation and experimental test of unsteady flow field for oscillating vanes gust generator in high-speed wind tunnel

Abstract

References

Catalog

Article Metrics

Related

Numerical simulation and experimental test of unsteady flow field for oscillating vanes gust generator in high-speed wind tunnel

Abstract

References

Catalog

Article Metrics

Related

Export File

Citation

Format

Content