Experimental research and analysis of gust generator for low speed wind tunnel

QU Xiaoli; LIU Qin; ZHU Bo; NIE Xutao; WANG Chao

doi:10.11729/syltlx20200114

Volume 35 Issue 5

Nov. 2021

Turn off MathJax

Article Contents

Article Navigation > Journal of Experiments in Fluid Mechanics > 2021 > 35(5): 99-105

QU X L，LIU Q，ZHU B，et al. Experimental research and analysis of gust generator for low speed wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2021，35（5）：99-105. doi: 10.11729/syltlx20200114

Citation:

PDF( 6531 KB)

Experimental research and analysis of gust generator for low speed wind tunnel

doi: 10.11729/syltlx20200114

QU Xiaoli^{1, 2
,},
LIU Qin^{2
,
,},
ZHU Bo²,
NIE Xutao²,
WANG Chao²

1.
State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang Sichuan　621000, China
2.
Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan　621000, China

Received Date: 2020-10-12
Rev Recd Date: 2021-01-20

Available Online: 2021-11-15

Publish Date: 2021-11-05

Abstract

Abstract

The gust generator is the key equipment for the wind tunnel test in response to the gust. According to the operating characteristics of the oscillating vanes gust generator, a simplified steady vortex theory is used to deduce the calculation formula of the Y-direction wind speed in the downstream flow field of the gust generator. With the experimental researches done in the 0.55 m × 0.4 m low-speed wind tunnel (a pilot acoustic wind tunnel), the influences on the extreme wind speed of the gust flow field were systematically studied by changing the design parameters of the gust generator (vane chord length, number, spacing) and operating parameters (vane swing amplitude, swing frequency, incoming flow velocity). The research shows that the simplified formula derived in this paper can explain the changing mechanism of the Y-direction wind speed in the downstream flow field after the design and operating parameters of the gust generator are changed. The gust flow field generated by the gust generator can be simply analyzed during the design of the gust generator. To increase the Y-speed extreme value of the downstream flow field of the gust generator, increasing the number of vanes has an advantage over increasing the vanes chord length. Before the vanes stall, the larger Y-speed extreme value can be obtained by increasing the vanes swing speed rather than by increasing the vanes swing frequency. The spacing of the vanes for the gust generator should not be too small, otherwise the equivalent lift coefficient of the vanes would decrease. When the vanes spacing is 1.2 times the chord length, the maximum Y-direction wind speed can be obtained. This research can provide reference for the design of gust generators in other wind tunnels.
- low speed wind tunnel,
- gust response,
- oscillating vanes,
- generator,
- experimental research

FullText(HTML)

References(23)

References

[1]	金长江, 肖业伦. 大气扰动中的飞行原理[M]. 北京: 国防工业出版社, 1992.
[2]	王亮,商霖,赵长见,等. 战术导弹的离散突风响应及动载荷计算研究[J]. 动力学与控制学报,2015,13(3):194-198. doi: 10.6052/1672-6553-2014-019 WANG L,SHANG L,ZHAO C J,et al. Study on the discrete gust dynamic load and reponses of tactics missiles[J]. Journal of Dynamics and Control,2015,13(3):194-198. doi: 10.6052/1672-6553-2014-019
[3]	吕继航,罗琳胤. 大型水陆两栖飞机突风响应特性的程序化设计[J]. 航空计算技术,2017,47(4):48-52. doi: 10.3969/j.issn.1671-654X.2017.04.012 LYV J H,LUO L Y. Gust response characteristic programming design of large amphibious aircraft[J]. Aeronautical Computing Technique,2017,47(4):48-52. doi: 10.3969/j.issn.1671-654X.2017.04.012
[4]	李建华,刘凯,李平坤,等. 低速长航时无人机垂直突风过载分析[J]. 航空工程进展,2017,8(3):304-307. LI J H,LIU K,LI P K,et al. Computation of longitudinal gust load for a low speed long endurance UAV[J]. Advances in Aeronautical Science and Engineering,2017,8(3):304-307.
[5]	BRZOZOWSKI D, CULP J, KUTAY A, et al. Closed-loop aerodynamic flow control of a free airfoil[C]//Proc of the 4th Flow Control Conference. 2008. doi: 10.2514/6.2008-4323.
[6]	胡海岩,赵永辉,黄锐. 飞机结构气动弹性分析与控制研究[J]. 力学学报,2016,48(1):1-27. doi: 10.6052/0459-1879-15-423 HU H Y,ZHAO Y H,HUANG R. Studies on aeroelastic analysis and control of aircraft structures[J]. Chinese Journal of Theoretical and Applied Mechanics,2016,48(1):1-27. doi: 10.6052/0459-1879-15-423
[7]	AZOULAY D, KARPEL M. Characterization of methods for com-putation of aeroservoelastic systems response to gust excitation[R]. AIAA-2006-1938, 2006. doi: 10.2514/6.2006-1938.
[8]	顾宁,陆志良,张家齐,等. 基于CFD的机翼突风响应计算[J]. 航空学报,2011,32(5):785-791. GU N,LU Z L,ZHANG J Q,et al. CFD-based analysis for gust response of aircraft wing[J]. Acta Aeronautica et Astronautica Sini-ca,2011,32(5):785-791.
[9]	詹浩,钱炜祺. 翼型和机翼阵风响应的数值模拟[J]. 空气动力学学报,2007,25(4):531-536. doi: 10.3969/j.issn.0258-1825.2007.04.022 ZHAN H,QIAN W Q. Numerical simulation of gust response for airfoil and wing[J]. Acta Aerodynamica Sinica,2007,25(4):531-536. doi: 10.3969/j.issn.0258-1825.2007.04.022
[10]	詹浩,钱炜祺. 弹性机翼阵风响应数值计算方法[J]. 计算力学学报,2009,26(2):270-275. doi: 10.7511/jslx20092021 ZHAN H,QIAN W Q. Numerical simulation on gust response of elastic wing[J]. Chinese Journal of Computational Mechanics,2009,26(2):270-275. doi: 10.7511/jslx20092021
[11]	MCKENZIE J. B-52 control configured vehicles ride control analysis and flight test[R]. AIAA-1973-782, 1973. doi: 10.2514/6.1973-782.
[12]	DISNEY T E. C-5A active load alleviation system[J]. Journal of Spacecraft and Rockets,1977,14(2):81-86. doi: 10.2514/3.57164
[13]	WINTHER B A,SHIRLEY W A,HEIMBAUGH R M. Wind-tunnel investigation of active controls technology applied to a DC-10 derivative[J]. Journal of Guidance and Control,1981,4(5):536-542. doi: 10.2514/3.56103
[14]	陈磊,吴志刚,杨超,等. 多控制面机翼阵风减缓主动控制与风洞试验验证[J]. 航空学报,2009,30(12):2250-2256. doi: 10.3321/j.issn:1000-6893.2009.12.002 CHEN L,WU Z G,YANG C,et al. Active control and wind tunnel test verification of multi-control surfaces wing for gust alleviation[J]. Acta Aeronautica et Astronautica Sinica,2009,30(12):2250-2256. doi: 10.3321/j.issn:1000-6893.2009.12.002
[15]	杨俊斌,吴志刚,戴玉婷,等. 飞翼布局飞机阵风减缓主动控制风洞试验[J]. 北京航空航天大学学报,2017,43(1):184-192. YANG J B,WU Z G,DAI Y T,et al. Wind tunnel test of gust alleviation active control for flying wing configuration aircraft[J]. Journal of Beijing University of Aeronautics and Astronautics,2017,43(1):184-192.
[16]	魏德宸,史志伟,彭仁明. 柔性翼微型飞行器垂直阵风响应特性的实验研究[J]. 实验流体力学,2012,26(4):38-42. doi: 10.3969/j.issn.1672-9897.2012.04.008 WEI D C,SHI Z W,PENG R M. Experimental investigation on the vertical gust response characteristics of the MAV with flexible structure[J]. Journal of Experiments in Fluid Mechanics,2012,26(4):38-42. doi: 10.3969/j.issn.1672-9897.2012.04.008
[17]	杨希明,刘南,郭承鹏,等. 飞行器气动弹性风洞试验技术综述[J]. 空气动力学学报,2018,36(6):995-1008. doi: 10.7638/kqdlxxb-2018.0039 YANG X M,LIU N,GUO C P,et al. A survey of aeroelastic wind tunnel test techonlogy of flight vehicles[J]. Acta Aerodynamica Sinica,2018,36(6):995-1008. doi: 10.7638/kqdlxxb-2018.0039
[18]	GREENBLATT D. Unsteady low-speed wind tunnels[J]. AIAA Journal,2016,54(6):1817-1830. doi: 10.2514/1.j054590
[19]	SADDINGTON A J,FINNIS M V,KNOWLES K. The characterisation of a gust generator for aerodynamic testing[J]. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering,2015,229(7):1214-1225. doi: 10.1177/0954410014548237
[20]	GRISSOM D, DEVENPORT W. Development and testing of a deterministic disturbance generator[R]. AIAA- 2004-2956, 2004. doi: 10.2514/6.2004-2956.
[21]	刘晓燕,吴志刚,杨超,等. 阵风发生器流场特性分析与试验验证[J]. 北京航空航天大学学报,2010,36(7):803-807. LIU X Y,WU Z G,YANG C,et al. Flow field analysis and experimental investigation on gust generator[J]. Journal of Beijing University of Aeronautics and Astronautics,2010,36(7):803-807.
[22]	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.
[23]	屈晓力,余永生,廖达雄,等. 声学引导风洞高效低噪声风扇设计[J]. 实验流体力学,2013,27(3):103-107, 112. doi: 10.3969/j.issn.1672-9897.2013.03.020 QU X L,YU Y S,LIAO D X,et al. The design of the high-performance low-noise fan of the acoustic pilot wind tunnel[J]. Journal of Experiments in Fluid Mechanics,2013,27(3):103-107, 112. doi: 10.3969/j.issn.1672-9897.2013.03.020