Test technology on unsteady characteristics of inlet flow during fighter plane maneuvers

Wu Chaojun; Nie Bowen; Kong Peng; Lu Xiangyu

doi:10.11729/syltlx20160027

Volume 31 Issue 2

Turn off MathJax

Article Contents

Abstract

References

Journal of Experiments in Fluid Mechanics > 2017 > 31(2): 98-104. > DOI: 10.11729/syltlx20160027

Wu Chaojun, Nie Bowen, Kong Peng, Lu Xiangyu. Test technology on unsteady characteristics of inlet flow during fighter plane maneuvers[J]. Journal of Experiments in Fluid Mechanics, 2017, 31(2): 98-104. DOI: 10.11729/syltlx20160027

Citation:

PDF (4618 KB)

Test technology on unsteady characteristics of inlet flow during fighter plane maneuvers

China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

More Information

Received Date: February 01, 2016
Revised Date: October 08, 2016

Graphical Abstract

Abstract

Abstract

A test facility was developed in the Φ3.2m wind tunnel, which is driven by two moment electromotors and used to simulate inlet working conditions of the fighter during high maneuvers. The unsteady test method for research on the inlet flow characteristics was established. Based on results of the validating test, the inlet flow characteristics during maneuvers with rapidly changing angle of attack were studied. Some unsteady features, such as the circumferential distortion and turbulence, were obtained from the tests. All these results prove the feasibility of the test technology on studying the unsteady characteristics of the fighter plane inlet flow during maneuvers in the low speed wind tunnel.
- fighter plane,
- inlet,
- unsteady,
- test technology,
- distortion

FullText(HTML)

References (13)

References

[1]	McCallum B. F-16 inlet stability investigation[R]. AIAA-89-2465, 1989.
[2]	Norby W P, Hleffele B A, Burley R R. Isolated testing of highly maneuverable inlet concepts[R]. NASA Contractor Report-179544, 1986.
[3]	Walsh K R, Yuhas A J, Williams J G, et al. Inlet distortion for an F/A-18A aircraft during steady aerodynamic conditions up to 60ångle of attack[R]. NASA Technical Memorandum 104329, 1997.
[4]	Yuhas A J, Steenken W G, Williams J G, et al. F/A-18A inlet flow characteristics during maneuvers with rapidly changing angle of attack[R]. NASA Technical Memorandum 104327, 1997.
[5]	Steenken W G, Williams J G, Yuhas A J, et al. Factors affecting inlet-engine compatibility during aircraft departures at high angle of attact for an F/A-18A aircraft[R]. NASA/TM-206572, 1999.
[6]	Steenken W G, Williams J G, Yuhas A J, et al. An inlet distortion assessment during aircraft departures at high angle of attack for an F/A-18A aircraft[R]. NASA Technical Memorandum 104328, 1997.
[7]	李周复.风洞特种试验技术[M].北京:航空工业出版社, 2010.
[8]	高静, 郝卫东, 闫永昌, 等.进气道低速特性试验技术研究[J].流体力学实验与测量, 2004, 18(1):38-42. http://www.cnki.com.cn/Article/CJFDTOTAL-LTLC200401009.htm Gao J, Hao W D, Yan Y C, et al. Experimental investigation on low speed characteristics of inlet[J]. Experiments and Mea-surements in Fluid Mechanics, 2004, 18(1):38-42. http://www.cnki.com.cn/Article/CJFDTOTAL-LTLC200401009.htm
[9]	杨应凯. Bump进气道设计与试验研究[J].空气动力学学报, 2007, 25(3):336-338. http://www.cnki.com.cn/Article/CJFDTOTAL-KQDX200703010.htm Yang Y K. The research of bump inlet design and test[J]. Acta Aerodynamic Sinica, 2007, 25(3):336-338. http://www.cnki.com.cn/Article/CJFDTOTAL-KQDX200703010.htm
[10]	刘凯礼, 张堃元.迎角动态变化对二元高超声速进气道气动特性的影响[J].航空学报, 2010, 31(4):709-714. http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201004010.htm Liu K L, Zhang K Y. Effect of dynamic angle of attack on unsteady aerodynamic characteristics of 2D hypersonic inlet[J]. Acta Aeronautica et Astronautica Sinica, 2010, 31(4):709-714. http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201004010.htm
[11]	杨应凯.飞机快速俯仰机动下Bump进气道的动态特性研究[J].实验流体力学, 2013, 27(6):39-42. http://www.syltlx.com/CN/abstract/abstract10411.shtml Yang Y K. The study on bump inlet dynamic characteristics under aircraft fast pitching maneuver[J]. Journal of Experiments in Fluid Mechanic, 2013, 27(6):39-42. http://www.syltlx.com/CN/abstract/abstract10411.shtml
[12]	赵海刚, 屈霁云, 史建邦, 等.高机动飞行下进气道/发动机相容性试验[J].航空动力学报, 2010, 25(9):2077-2082. http://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201009024.htm Zhao H G, Qu J Y, Shi J B, et al. Filghting test of inlet/engine compatibility during rapidly changing aircraft maneuvers[J]. Journal of Aerospace Power, 2010, 25(9):2077-2082. http://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201009024.htm
[13]	恽起麟.风洞实验[M].北京:国防工业出版社, 2009.

[1]	DONG Lin, WEN Guoan, LEI Ziwei, RINOSHIKA Akira. PIV experimental study on vortex structures induced by free autorotation fall of a samaras[J]. Journal of Experiments in Fluid Mechanics, 2021, 35(5): 54-60. DOI: 10.11729/syltlx20200004
[2]	FU Hao, HE Chuangxin, LIU Yingzheng. PIV experimental study on flow characteristics of a low swirl number precessing jet[J]. Journal of Experiments in Fluid Mechanics, 2021, 35(3): 39-45. DOI: 10.11729/syltlx20200129
[3]	WANG Fujun, WANG Hongping, GAO Qi, WEI Runjie, LIU Yanpeng. PIV experimental study on fish swimming vortex structure[J]. Journal of Experiments in Fluid Mechanics, 2020, 34(5): 20-28. DOI: 10.11729/syltlx20200039
[4]	SHEN Feng, YAN Chengjin, LI Mengqi, JI Deru, LIU Zhaomiao. Micro-PIV study on flow field characteristics of droplets in a microcavity[J]. Journal of Experiments in Fluid Mechanics, 2020, 34(2): 67-72. DOI: 10.11729/syltlx20190117
[5]	Zhang Jun, Bai Yaqiang, Zhai Shucheng, Zhang Guoping, Xu Lianghao. PIV measurement on streamwise vortex generated by undulating fins[J]. Journal of Experiments in Fluid Mechanics, 2017, 31(6): 15-21. DOI: 10.11729/syltlx20170017
[6]	Liu Ping'an, Lin Yongfeng, Chen Yaofeng, Yuan Mingchuan. Blade tip vortex measurements of a hovering rotor[J]. Journal of Experiments in Fluid Mechanics, 2017, 31(4): 39-44. DOI: 10.11729/syltlx20160186
[7]	Wu Jinhua, Sun Haisheng, Shen Zhihong, Jiang Yubiao. 旋转流场下的振荡动导数试验技术研究[J]. Journal of Experiments in Fluid Mechanics, 2014, (4): 54-58. DOI: 10.11729/syltlx20130057
[8]	WU Wen-fei, XIE Jing-xing, GONG Zhi-jun, LI Bao-wei. PIV measurements of the turbulence integral length scale on cold combustion flow field in burner zone of tangential firing boiler[J]. Journal of Experiments in Fluid Mechanics, 2012, 26(2): 38-41,50. DOI: 10.3969/j.issn.1672-9897.2012.02.008
[9]	LI Hao, LIN Ming, ZHANG Yu-shan, SHEN Ji-kui, CHEN Chun-de. Study on centeral-dump combustor by PIV[J]. Journal of Experiments in Fluid Mechanics, 2011, 25(4): 45-49,59. DOI: 10.3969/j.issn.1672-9897.2011.04.009
[10]	ZHANG Xiao-di, JIANG Jia-li, JIA Yuan-sheng, MA Hong-zhi, XIAO Ya-ke. Measurements of cylinder's wake by PIV[J]. Journal of Experiments in Fluid Mechanics, 2005, 19(2): 74-78. DOI: 10.3969/j.issn.1672-9897.2005.02.015

Cited By

Cited by

Periodical cited type(1)

张怀宝，王靖宇，Bailey Sean C.C.，王光学，邓小刚. 低雷诺数壁面约束流动皮托管测速误差分析与校正. 国防科技大学学报. 2018(03): 37-41 .

Other cited types(0)

Get Citation

PDF

XML

Article Metrics

Article views (174) PDF downloads (19) Cited by(1)

Test technology on unsteady characteristics of inlet flow during fighter plane maneuvers

Abstract

References

Related Articles

Cited by

Periodical cited type(1)

Other cited types(0)

Catalog

Article Metrics

Related

Test technology on unsteady characteristics of inlet flow during fighter plane maneuvers

Abstract

References

Related Articles

Cited by

Periodical cited type(1)

Other cited types(0)

Catalog

Article Metrics

Related

Export File

Citation

Format

Content