Aerodynamic force and moment measurement of 10° half-angle cone in JF12 shock tunnel
查看参考文献16篇
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文摘
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An aerodynamic force and moment measurement was conducted in JF12 long-testduration detonation-driven shock tunnel of Institute of Mechanics, Chinese Academy of Sciences. The test duration of JF12 is 100–130 ms. The nominal Mach number is 7.0 and the exit diameter of the contoured nozzle is 2.5 m. The total enthalpy is 2.5 MJ/kg which duplicates the hypersonic flight conditions of Mach number 7.0 at 35 km altitude. The test model is the standard aerodynamic force model of 10° half-angle sharp cone. The length of the test model is 1500 mm and the weight is 57 kg. The aerodynamic forces were measured with a six-component strain balance. The angles of attack were set to be-5°, 0°, 5°, 10° and 14°, respectively. The experimental results show that in the 100– 130 ms test duration, the signals of strain balance have 3–4 complete vibration cycles. So, the aerodynamic forces and moments can be obtained directly by averaging the signals of balance without acceleration compensation. The force measurement error of repeatability of JF12 is less than 2%. The aerodynamic force coefficients of JF12 are in good agreement with those of conventional hypersonic wind tunnels. For this test model at Mach number 7.0 and total enthalpy of 2.5 MJ/ kg, the real-gas effects on aerodynamic force characteristics are not very evident. |
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来源
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Chinese Journal of Aeronautics
,2017,30(3):983-987 【核心库】
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DOI
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10.1016/j.cja.2017.02.008
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关键词
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Aerodynamic force and moment measurement
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10° half-angle cone model
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JF12
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Real-gas effects
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Shock tunnel
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地址
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Institute of Mechanics, Chinese Academy of Sciences, State Key Laboratory of High Temperature Gas Dynamics, Beijing, 100190
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语种
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英文 |
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文献类型
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研究性论文 |
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ISSN
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1000-9361 |
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学科
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航空 |
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基金
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国家自然科学基金
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文献收藏号
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CSCD:6004701
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参考文献 共
16
共1页
|
|
1.
Bertin J J. Critical hypersonic aerothermodynamic phenomena.
Ann Rev Fluid Mech,2006,38(1):129-157
|
被引
51
次
|
|
|
|
|
2.
Woods W C. A review of preflight estimates of real-gas effects on space shuttle aerodynamic characteristics.
Shuttle performance: Lessons learned,1983
|
被引
1
次
|
|
|
|
|
3.
Maus J R. Hypersonic mach number and real gas effects on space shuttle orbiter aerodynamic.
J Spacecraft Rockets,1984,21(2):136-141
|
被引
7
次
|
|
|
|
|
4.
Park C. Hypersonic aerothermodynamics: Past, present and future.
Int'l J of Aeronautical & Space Sci,2013,14(1):1-10
|
被引
4
次
|
|
|
|
|
5.
Park C. Evaluation of real-gas phenomena in high-enthalpy impulse test facilities: A review.
Journal of Thermophysics and Heat Transfer,1997,11(1):10-18
|
被引
2
次
|
|
|
|
|
6.
Lu F K. Advanced hypersonic test facilities.
Prog Astronaut Aeronaut,1971,1:64
|
被引
1
次
|
|
|
|
|
7.
Abbott C D.
Status of AEDC transonic, supersonic, and hypersonic wind tunnel improvement programs. Report No.: AIAA-2012-3172,2012
|
被引
1
次
|
|
|
|
|
8.
Tang Z G. Research progress on hypersonic wind tunnel aerodynamic testing techniques.
Acta Aeronaut Astronaut Sin. [Chinese],2015,36(1):86-97
|
被引
2
次
|
|
|
|
|
9.
Bertin J J. Fifty years of hypersonics: where we’ve been, where we’re going.
Prog Aerospace Sci,2003,39(6/7):511-536
|
被引
76
次
|
|
|
|
|
10.
Bushnell D M. Scaling: Wind tunnel to flight.
Annu Rev Fluid Mech,2006,38:111-128
|
被引
5
次
|
|
|
|
|
11.
Chen J Q. Review of correlation analysis of aerodynamic data between flight and ground prediction for hypersonic vehicle.
Acta Aerodynamica Sin. [Chinese],2014,32(5):587-599
|
被引
1
次
|
|
|
|
|
12.
Jiang Z.
Experiments and development of long-testduration hypervelocity detonation-driven shock tunnel (LHDst). Report No.: AIAA-2014-1012,2014
|
被引
1
次
|
|
|
|
|
13.
Dufrene A.
Extension of LENS shock tunnel text times and lower mach number capability. Report No.: AIAA-2015-2017,2015
|
被引
1
次
|
|
|
|
|
14.
Luo Y F. The accelerometer force balance used in the impulse wind tunnel.
Aerodynamic Exp Meas Control. [Chinese],1996,10(1):59-63
|
被引
1
次
|
|
|
|
|
15.
Sahoo N. An accelerometer balance system for measurement of aerodynamic force coefficient over blunt bodies in a hypersonic shock tunnel.
Measurement Science and Technology,2003,14:260-272
|
被引
9
次
|
|
|
|
|
16.
Chen H. Investigation on the link-up between the aerodynamic force data measured in supersonic and hypersonic wind tunnel.
Acta Aerodynamica Sin. [Chinese],2002,18(3):345-349
|
被引
1
次
|
|
|
|
|
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