高超声速飞行器DPIV内流阻力测量技术研究

推进技术 ›› 2014, Vol. 35 ›› Issue (4): 455-462.

高超声速飞行器DPIV内流阻力测量技术研究

黄湛,王宏伟,张妍,张江,宫建

中国航天空气动力技术研究院,北京 100074;中国航天空气动力技术研究院,北京 100074;中国航天空气动力技术研究院,北京 100074;中国航天空气动力技术研究院,北京 100074;中国航天空气动力技术研究院,北京 100074

发布日期:2021-08-15
作者简介:黄湛(1969—),男,博士,副研究员,研究领域为实验空气动力学,流动显示测量技术及可压缩剪切流。 E-mail:xunfang05@sohu.com

Research of Internal Drag DPIV Measurement for Hypersonic Vehicle

China Academy of Aerospace Aerodynamic, Beijing 100074, China;China Academy of Aerospace Aerodynamic, Beijing 100074, China;China Academy of Aerospace Aerodynamic, Beijing 100074, China;China Academy of Aerospace Aerodynamic, Beijing 100074, China;China Academy of Aerospace Aerodynamic, Beijing 100074, China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究吸气式高超声速飞行器的气动特性,提出一种新的内流阻力测量技术,即采用粒子图像测速技术和总压测量技术相结合,测量超燃发动机尾喷管流场速度矢量和皮托压力分布,间接获得内流出口处平均马赫数和内流出口处静压平均值,从而实现高超声速通气模型内流阻力测量。研究结果表明:粒子图像测速技术和总压测量技术相结合,成功地实现了内流阻力测量；试验获得的粒子图像,能够清楚地显示喷管出口位置内外流的分界面及边界层和边界层的尾迹；粒子图像测速试验获得的速度矢量场结果准确,精度高,能够提供远远超出传统测量技术所能提供的流场信息。 

关键词: 飞行器;通气模型;高超声速;内阻测量 

Abstract: To research aerodynamic characteristics of hypersonic vehicle with air-breathing inlet, a new measurement method of internal drag was proposed. Through the combination of DPIV and total pressure rake which were applied to measure velocity field and pitot pressure field of outlet flow,respectively,from scramjet nozzle, mean Mach number and mean static pressure can be computed indirectly, and internal drag measurement of hypersonic flow through model was achieved. The research results show that the new measurement method successfully measure internal drag of hypersonic flow through model. The particle images of DPIV can clearly display the interface between internal and external flow and the wakes of boundary layer. DPIV can supply accurate velocity fields which possess more information than measurement results of traditional test technique. 

Key words: Flight Vehicle; Flow through model; Hypersonic; Internal drag measurement

黄湛,王宏伟,张妍,张江,宫建. 高超声速飞行器DPIV内流阻力测量技术研究[J]. 推进技术, 2014, 35(4): 455-462.

HUANG Zhan, WANG Hong-wei, ZHANG Yan, ZHANG Jiang, GONG Jian. Research of Internal Drag DPIV Measurement for Hypersonic Vehicle[J]. Journal of Propulsion Technology, 2014, 35(4): 455-462.

参考文献

[1] William J Small, John P Weidner,Jobnston P J.Scramjet Nozzle Design and Analysis as Applied to a Highly Integrated Hypersonic Research Airplane[R].NASA TN D-8334,6.
[2] 张艳慧,徐惊雷,张堃元.超燃冲压发动机非对称喷管设计点性能[J]．推进技术,2007, 28(3):282-286．(ZHANG Jing-Hui, XU Jing-Lei, ZHANG Kun-Yuan.Numerical Simulation of Single Expansion Ramp Nozzle for Scramjet on the Designing Point [J].Journal of Propulsion Technology, 2007,8(3):282-286.)
[3] Holland Scott D,Woods William C,Engelund Walter C．Hyper-X Research Vehicle Experimental Aerodynamics Test Program Overview[J]． Journal of Spacecraft and Rockets, 2001, 38(6) :11-12．
[4] 张红英,孙姝,程克明,等．进气道工作状态对吸气式高超声速飞行器气动力特性影响的实验研究[J]．宇航学报, 2007, 28(6) :1488-1493．
[5] 张红英,程克明,伍贻兆．某高超飞行器流道冷流特征及气动力特性研究[J]．空气动力学学报,2009,27(1):119-123．
[6] Huebner Lawrence D,Witte David W． Exhaust Simulation Testing of a Hypersonic Airbreathing Model at Transonic Speeds[R]．AIAA 2003-7001．
[7] 范洁川.风洞试验手册[M].北京:航空工业出版社,2002.
[8] 程厚梅.风洞实验干扰与修正[M].北京:国防工业出版社,2003.
[9] 张覃钧.再谈飞机进气道通气模型的高速风洞实验[J].气动研究与发展,1978,(5):39-59.
[10] 张覃钧.飞机进气道通气模型的高速风洞实验[R].北京:航空航天工业部,1989.
[11] Adrian R J.Particle Imagine Techniques for Experimental Fluid Mechanics[J].Ann.Rev.Fluid Mech., 1991,3:261-304.
[12] 田立丰, 易仕和, 赵玉新,等.超声速光学头罩流场的PIV研究[J].实验流体力学, 2010,4(1):26-29.
[13] 黄湛, 王宏伟, 姚开明,等.亚跨超声速风洞中采用粒子图像测速技术进行飞机机头高速选型实验[J].实验流体力学, 2012,6(6):30-34.
[14] Sahoo D, Desai P, Smits A.Experimental Investigation of Helium Injection in a Hypersonic Turbulent Boundary Layer[R].AIAA 2010-1559.
[15] VAN der Draai R K,Scarano F,Feenstra G J, et al.Application of PIV in (Local) Supersonic Flows in DNW Wind Tunnels[R].AIAA 2005-4082.
[16] Haertig J,Havermann M,Ray C,et al.PIV measurements in Mach 3.5and 4.5Shock Tunnel Flow[R].AIAA 2001-0699.
[17] 黄湛,张江, 宫建,等.通气模型超音速DPIV实验研究[C].北京:第八届全国实验流体力学学术会议论文集, 2010:58-63.