重气体介质的等熵流动特性

刘永平; 寇西平; 查俊; 余立; 路波

doi:10.13224/j.cnki.jasp.20230421

重气体介质的等熵流动特性

doi: 10.13224/j.cnki.jasp.20230421

刘永平^1,,
寇西平^{1, 2},
查俊¹,
余立¹,
路波^1,*, ,

1.
中国空气动力研究与发展中心高速空气动力研究所，四川绵阳 621000
2.
西北工业大学航空学院，西安 710072

基金项目: 四川省自然科学基金（2023NSFSC0400）

详细信息

作者简介:
刘永平（1991-），男，博士生，主要从事飞行器气动弹性力学研究。E-mail：liuyp917@163.com

通讯作者:
路波（1964-），男，研究员级高级工程师，硕士，主要从事飞行器气动弹性力学研究。E-mail：lubo@cadc.cn

中图分类号: V211.24
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出版历程
- 收稿日期: 2023-06-26
- 网络出版日期: 2025-07-01

Isentropic flow characteristics of heavy gas medium

LIU Yongping^1
,,
KOU Xiping^{1, 2},
ZHA Jun¹,
YU Li¹,
LU Bo^{1,*
, ,}

1.
High Speed Aerodynamics Institute，China Aerodynamics Research and Development Center，Mianyang Sichuan 621000，China
2.
School of Aeronautics，Northwestern Polytechnical University，Xi’an 710072，China

摘要

摘要:
为研究重气体介质在高速风洞中的可压缩流场特性及相关的影响因素，在典型工况下考虑重气体介质真实的气体效应，基于一维等熵流动理论计算了给定总压、总温和一系列自由流马赫数下重气体介质的等熵流动特性。计算结果表明：在较高的总温状态下重气体四氟乙烷（R-134a）和六氟化硫（SF₆）的气体压缩因子Z接近1，定总温总压下在来流马赫数0.3～1.3的亚跨声速范围内比热比γ基本恒定，能够将重气体视作量热完全气体，视为量热完全气体所导致的马赫数计算偏差小于0.3%，满足风洞马赫数控制的要求。从翼型高速绕流的角度，重气体与空气等熵流流场参数的分析表明流场静温的较大差异将引起重气体与空气风洞试验数据的偏差，进而需要对重气体下获得的试验数据进行相应转化，该研究为后续重气体介质中飞行器气动特性研究及气动数据修正方法的发展提供了基础支持。
- 重气体介质 /
- 真实气体效应 /
- 等熵流动 /
- 风洞 /
- 马赫数控制
Abstract:
In order to study the compressible flow field characteristics of heavy gas medium in high-speed wind tunnel and its related influencing factors, the real gas effect of heavy gas medium was considered, and based on one-dimensional isentropic flow theory, the flow field parameters for a specified set of free-stream Mach numbers under the given total pressure and total temperature were calculated under wind tunnel typical operating conditions. The calculation results showed that the gas compression factor Z was close to 1 for heavy gas tetrafluoroethane (R-134a) and sulfur hexafluoride (SF₆) at higher total temperature, and the specific heat ratio γ was basically constant at certain total temperature and total pressure within the range of free-stream Mach number from 0.3 to 1.3, and it was possible to consider the heavy gas both thermally and calorically perfect. Under the certain condition of total temperature and total pressure, the Mach number deviation obtained by treating heavy gas both thermally and calorically perfect was less than 0.3%, which met the requirements of wind tunnel Mach number control. In view of the high-speed flow around the airfoil, the analysis of flow field parameters of isentropic flow between heavy gas and air showed that the large difference of static temperature of flow field may cause the deviation of wind tunnel test data between heavy gas and air, and then the test data obtained under heavy gas shall be transformed accordingly. This could provide a basic support for subsequent research on aerodynamic characteristics of aircraft in heavy gas medium and the development of aerodynamic data correction methods.
- heavy gas medium /
- real gas effect /
- isentropic flow /
- wind tunnel /
- Mach number control

HTML

图 1 R-134a的γ～T_l曲线

Figure 1. Curves of γ～T_l for R-134a

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图 2 空气的Z～Ma曲线（T_t=300 K）

Figure 2. Curves of Z～Ma for air （T_t=300 K）

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图 3 空气的γ～Ma曲线（T_t=300 K）

Figure 3. Curves of γ～Ma for air （T_t=300 K）

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图 4 空气的T_l/T_t～Ma曲线（T_t=300 K）

Figure 4. Curves of T_l/T_t～Ma for air （T_t=300 K）

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图 5 空气的p_l/p_t～Ma曲线（T_t=300 K）

Figure 5. Curves of p_l/p_t～Ma for air （T_t=300 K）

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图 6 相同总温不同总压下Z～Ma曲线

Figure 6. Curves of Z～Ma under same total temperature with different total pressure

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图 7 相同总温不同总压下γ～Ma曲线

Figure 7. Curves of γ～Ma under same total temperature with different total pressure

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图 8 相同总温不同总压下p_l/p_t～Ma曲线（T_t=323 K）

Figure 8. Curves of p_l/p_t～Ma under same T_t with different p_t （T_t=323 K）

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图 9 相同总温不同总压下T_l/T_t～Ma曲线（T_t=323 K）

Figure 9. Curves of T_l/T_t～Ma under same T_t with different p_t （T_t=323 K）

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图 10 马赫数偏差（T_t=300 K，p_t=10 132.5 Pa）

Figure 10. Deviation of the Mach number （T_t=300 K，p_t=10 132.5 Pa）

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表 1 真实气体物理属性参考文献

Table 1. References of Real gas physical properties

气体状态方程（EOS）

R-134a Tillner-Roth等^[23]
SF₆ Guder等^[24]
Air Lemmon等^[25]

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表 2 总温和总压工况

Table 2. Operating condition of T_t and p_t

总温T_t/K 总压p_t/Pa

303 5066.25、10132.5、50662.5、
75993.75、101325、126656.25

323

343

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参考文献(25)

[1]	李秋彦, 李刚, 魏洋天, 等. 先进战斗机气动弹性设计综述[J]. 航空学报, 2020, 41(6): 523430. LI Qiuyan, LI Gang, WEI Yangtian, et al. Review of aeroelasticity design for advanced fighter[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(6): 523430. (in Chinese LI Qiuyan, LI Gang, WEI Yangtian, et al. Review of aeroelasticity design for advanced fighter[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(6): 523430. (in Chinese)
[2]	杨超, 黄超, 吴志刚, 等. 气动伺服弹性研究的进展与挑战[J]. 航空学报, 2015, 36(4): 1011-1033. YANG Chao, HUANG Chao, WU Zhigang, et al. Progress and challenges for aeroservoelasticity research[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(4): 1011-1033. (in Chinese YANG Chao, HUANG Chao, WU Zhigang, et al. Progress and challenges for aeroservoelasticity research[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(4): 1011-1033. (in Chinese)
[3]	罗务揆, 谭申刚, 谢怀强, 等. 确定颤振模型设计参数的方法研究[J]. 航空学报, 2013, 34(10): 2383-2390. LUO Wukui, TAN Shengang, XIE Huaiqiang, et al. Research on methods used to determine flutter model design factors[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(10): 2383-2390. (in Chinese LUO Wukui, TAN Shengang, XIE Huaiqiang, et al. Research on methods used to determine flutter model design factors[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(10): 2383-2390. (in Chinese)
[4]	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. YANG Ximing, LIU Nan, GUO Chengpeng, et al. A survey of aeroelastic wind tunnel test techonlogy of flight vehicles[J]. Acta Aerodynamica Sinica, 2018, 36(6): 995-1008. (in Chinese doi: 10.7638/kqdlxxb-2018.0039 YANG Ximing, LIU Nan, GUO Chengpeng, et al. A survey of aeroelastic wind tunnel test techonlogy of flight vehicles[J]. Acta Aerodynamica Sinica, 2018, 36(6): 995-1008. (in Chinese) doi: 10.7638/kqdlxxb-2018.0039
[5]	IVANCO T G. Unique testing capabilities of the NASA Langley Transonic Dynamics Tunnel, an exercise in aeroelastic scaling: AIAA2013-2625 [R]. Reston, US: AIAA, 2013.
[6]	COLE S, GARCIA J. Past, present, and future capabilities of the Transonic Dynamics Tunnel from an aeroelasticity perspective: AIAA2000-1767 [R]. Reston, US: AIAA, 2000.
[7]	MUKHOPADHYAY V. Transonic flutter suppression control law design and wind-tunnel test results[J]. Journal of Guidance, Control, and Dynamics, 2000, 23(5): 930-937.
[8]	PENDLETON E W, BESSETTE D, FIELD P B, et al. Active aeroelastic wing flight research program: technical program and model analytical development[J]. Journal of Aircraft, 2000, 37(4): 554-561.
[9]	YEAGER W T, KVATERNIK R G. Contributions of the Langley transonic dynamics tunnel to rotorcraft technology and development[R]. AIAA-2000-1771, 2000.
[10]	COLE S R, KELLER D F, PIATAK D J. Contributions of the Transonic dynamics tunnel to launch vehicle and spacecraft development[R]. AIAA-2000-1772, 2000.
[11]	PERR B, NOLL T, SCOTT R. Contributions of the Transonic Dynamics Tunnel to the testing of active control of aeroelastic response: AIAA2000-1769 [R]. Reston, US: AIAA, 2000.
[12]	VON DOENHOFF A E, BRASLOW A L, SCHWARTZBERG M A. Studies of the use of Freon-12 as a wind tunnel testing medium: NACA-TN-3000[R]. Washington US: NACA, 1953.
[13]	SCHWARTZBERG M A. A study of the use of Freon-12 as a windtunnel testing medium at low supersonic Mach numbers: NACARM-L52J07[R]. Washington DC: NACA 1952.
[14]	VON DOENHOFF A E, BRASLOW A L. Studies of the use of Freon-12 as a testing medium in the Langley Low-Turbulence Pressure Tunnel: NACA-RM-L51I11 [R]. Washington DC: NACA, 1951.
[15]	STANLEY R, RIVERA J A. The new heavy gas testing capability in the NASA langley transonic dynamics tunnel[R]. Cambridge, US: Royal Aeronautical Society Forum Paper No. 4, 1997.
[16]	CORLISS J, COLE S. Heavy gas conversion of the NASA langley transonic dynamics tunnel: AlAA 98-2710 [R]. Reston, US: AIAA, 1998.
[17]	ANDERSON W. A numerical study on the use of sulfur hexafluoride as a test gas for wind tunnels: AIAA1990-1421[R]. Reston, US: AIAA, 1990.
[18]	BONHAUS D, ANDERSON W, MAVRIPLIS D. Numerical study to assess sulfur hexafluoride as a medium for testing multielement airfoils[R]. NASA-TP-3496, 1995.
[19]	ANDERS J, ANDERSON W, MURTHY A. The use of heavy gas for increased Reynolds numbers in transonic wind tunnels: AIAA1998-2882 [R]. Reston, US: AIAA, 1998.
[20]	张汇卓. 重气体环境机翼气动特性数值模拟研究[D]. 北京: 军事科学院, 2021. ZHANG Huizhuo. Numerical simulation study on aerodynamic characterristics of wing in heavy gas environment[D]. Beijing: Academy of Military Sciences, 2021. (in Chinese ZHANG Huizhuo. Numerical simulation study on aerodynamic characterristics of wing in heavy gas environment[D]. Beijing: Academy of Military Sciences, 2021. (in Chinese)
[21]	查俊, 曾开春, 寇西平, 等. 重气体介质中超临界翼型跨声速流动特性[J]. 航空动力学报, 2021, 36(9): 1894-1905. ZHA Jun, ZENG Kaichun, KOU Xiping, et al. Transonic flow characteristics of supercritical airfoil in heavy gas medium[J]. Journal of Aerospace Power, 2021, 36(9): 1894-1905. (in Chinese ZHA Jun, ZENG Kaichun, KOU Xiping, et al. Transonic flow characteristics of supercritical airfoil in heavy gas medium[J]. Journal of Aerospace Power, 2021, 36(9): 1894-1905. (in Chinese)
[22]	BELL I H, WRONSKI J, QUOILIN S, et al. Pure and pseudo-pure fluid thermophysical property evaluation and the open-source thermophysical property library CoolProp[J]. Industrial & Engineering Chemistry Research, 2014, 53(6): 2498-2508.
[23]	TILLNER-ROTH R, BAEHR H D. An international standard formulation for the thermodynamic properties of 1, 1, 1, 2-tetrafluoroethane (HFC-134a) for temperatures from 170 K to 455 K and pressures up to 70 MPa[J]. Journal of Physical and Chemical Reference Data, 1994, 23(5): 657-729.
[24]	GUDER C, WAGNER W. A reference equation of state for the thermodynamic properties of sulfur hexafluoride (SF6) for temperatures from the melting line to 625 K and pressures up to 150 MPa[J]. Journal of Physical and Chemical Reference Data, 2009, 38(1): 33-94. doi: 10.1063/1.3037344
[25]	LEMMON E W, JACOBSEN R T, PENONCELLO S G, et al. Thermodynamic properties of air and mixtures of nitrogen, argon, and oxygen from 60 to 2 000 K at pressures to 2 000 MPa[J]. Journal of Physical and Chemical Reference Data, 2000, 29(3): 331-385. doi: 10.1063/1.1285884