JF12长实验时间激波风洞10°尖锥气动力实验研究

刘云峰; 汪运鹏; 苑朝凯; 罗长童; 姜宗林

doi:10.19527/j.cnki.2096-1642.2017.02.001

JF12长实验时间激波风洞10°尖锥气动力实验研究

doi: 10.19527/j.cnki.2096-1642.2017.02.001

刘云峰^{1, 2,},
汪运鹏^{1, 2},
苑朝凯^{1, 2},
罗长童^{1, 2},
姜宗林^{1, 2}

1.
中国科学院力学研究所高温气体动力学国家重点实验室，北京 100190
2.
中国科学院大学工程科学学院，北京 100049

基金项目:

国家自然科学基金 11672312

国家自然科学基金 11532014

详细信息

作者简介:
刘云峰(1971-)男, 山东龙口, 副研究员, 研究方向为高温气体动力学.通信地址:北京北四环西路15号(100190).E-mail:liuyunfeng@imech.ac.cn

中图分类号: V211.22
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出版历程
- 收稿日期: 2016-11-26
- 修回日期: 2017-02-01
- 发布日期: 2017-03-20
- 刊出日期: 2017-03-01

Aerodynamic Force Measurements of 10° Half-Angle Cone in JF12 Long-Test-Time Shock Tunnel

LIU Yun-feng^{1, 2
,},
WANG Yun-peng^{1, 2},
YUAN Chao-kai^{1, 2},
LUO Chang-tong^{1, 2},
JIANG Zong-lin^{1, 2}

1.
State Key Laboratory of High-Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China
2.
School of Engineering Sciences, University of Chinese Academy of Sciences, Beijng 100049, China

摘要

摘要: 介绍了在中国科学院力学研究所JF12长实验时间激波风洞上开展的10°尖锥标模的天平测力实验研究结果.JF12激波风洞的实验时间为100~130 ms，名义Mach数为7.0，喷管出口直径为2.5 m，总焓为2.5 MJ/kg，复现了35 km高空的飞行条件.采用六分量应变天平，攻角分别为-5，0，5，10和14°，模型长度为1.5 m，质量为50 kg.实验结果表明，在100~130 ms的实验时间里，应变天平的输出信号含有3~4个完整周期，可以通过对天平的输出信号进行平均直接获得气动力/矩测量结果，而不再需要进行加速度补偿，且气动力系数重复测量的不确定度小于2%.JF12激波风洞气动力系数的测量结果与传统高超声速风洞的结果符合得较好，表明在2.5 MJ/kg的总焓下，真实气体效应对该模型气动力特性的影响不明显.
- JF12长实验时间激波风洞 /
- 高超声速气动力特性 /
- 10°尖锥标模 /
- 真实气体效应
Abstract: Aerodynamic force and moment measurements were conducted in JF12 long-test-time detonation-driven shock tunnel of Institute of Mechanics, Chinese Academy of Sciences. The test time of JF12 was 100~130 ms. The nominal Mach number was 7.0 and the exit diameter of the contoured nozzle was 2.5 m. The total enthalpy was 2.5 MJ/kg which duplicated the hypersonic flight conditions of 35 km altitude. The test model was standard aerodynamic model of 10° half-angle sharp cone. The length of the test model was 1500 mm with a mass of 50 kg. The aerodynamic forces were measured with a six-component strain balance. The angle of attack was set to be -5, 0, 5, 10 and 14°. The experimental results show that in the 100~130 ms test time, the signal of strain balance has 3~4 complete cycles. So the aerodynamic forces can be obtained directly by averaging the signal of balance without acceleration compensation. The uncertainty of force measurement in JF12 is less than 2%. The aerodynamic force coefficients of JF12 are in good agreement with that of conventional hypersonic wind tunnels with a difference of less than 2%. For this model under total enthalpy of 2.5 MJ/kg, the real-gas effects on aerodynamic force characteristics are not very evident.
- JF12 long-test-time shock tunnel /
- hypersonic aerodynamic characteristics /
- 10°half-angle cone model /
- real-gas effects

HTML全文

图 1 JF12长实验时间激波风洞结构图

Figure 1. Schematic of JF12 long-test-time shock tunnel

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图 2 JF12长实验时间激波风洞照片

Figure 2. Photo of JF12 long-test-time shock tunnel

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图 3 10°尖锥模型

Figure 3. 10° half-angle cone model

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图 4 六分量应变天平

Figure 4. Six-component strain balance

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图 5 模型支撑系统的振动频率

Figure 5. Vibration frequencies of JF12 model supporting system

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图 6 天平俯仰力矩信号

Figure 6. Balance signal of pitch moment

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图 7 模型底部底压传感器布置图

Figure 7. Pressure transducers installed on bottom surface of test model

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图 8 天平信号和模型底压信号

Figure 8. Balance and pressure transducers output signals

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图 9 不同攻角下的法向力系数

Figure 9. Normal force coefficients at different attack angles

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图 10 不同攻角下的轴向力系数

Figure 10. Axial force coefficients at different attack angles

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图 11 不同攻角下的压心系数

Figure 11. Coefficients of pressure center at different attack angles

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参考文献(15)

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[6]	Park C. Hypersonic aerothermodynamics:past, present and future[J]. International Journal of Aeronautical and Space Sciences, 2013, 14(1):1-10. doi: 10.5139/IJASS.2013.14.1.1
[7]	Park C. Evaluation of real-gas phenomena in high-enthalpy impulse test facilities:a review[J]. Journal of Thermophysics and Heat Transfer, 1997, 11(1):10-18. doi: 10.2514/2.6217
[8]	Lu F K, Marren D E. Advanced hypersonic test facilities[M]. New York:AIAA, 2002.
[9]	Bertin J J, Cummings R M. Fifty years of hypersonics:where we've been, where we're going[J]. Progress in Aerospace Sciences, 2003, 39(6):511-536. https://www.researchgate.net/publication/222517414_Fifty_Years_of_Hypersonics_Where_We%27ve_Been_Where_We%27re_Going
[10]	Jiang Z, Yu H. Experiments and development of long-test-duration hypervelocity detonation-driven shock tunnel (LHDst)[R]. AIAA 2014-1012, 2014.
[11]	Jiang Z L, Li J P, Zhao W, et al. Investigation into techniques for extending the test-duration of detonation-driven shock tunnels[J]. Chinese Journal of Theoretical and Applied Mechanics, 2012, 44(5):824-831.
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JF12长实验时间激波风洞10°尖锥气动力实验研究

doi: 10.19527/j.cnki.2096-1642.2017.02.001

作者简介:
刘云峰(1971-)男, 山东龙口, 副研究员, 研究方向为高温气体动力学.通信地址:北京北四环西路15号(100190).E-mail:liuyunfeng@imech.ac.cn

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Aerodynamic Force Measurements of 10° Half-Angle Cone in JF12 Long-Test-Time Shock Tunnel

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JF12长实验时间激波风洞10°尖锥气动力实验研究

doi: 10.19527/j.cnki.2096-1642.2017.02.001

作者简介: 刘云峰(1971-)男, 山东龙口, 副研究员, 研究方向为高温气体动力学.通信地址:北京北四环西路15号(100190).E-mail:liuyunfeng@imech.ac.cn

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Aerodynamic Force Measurements of 10° Half-Angle Cone in JF12 Long-Test-Time Shock Tunnel

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作者简介:
刘云峰(1971-)男, 山东龙口, 副研究员, 研究方向为高温气体动力学.通信地址:北京北四环西路15号(100190).E-mail:liuyunfeng@imech.ac.cn