重气体风洞试验数据修正方法综述

刘永平; 夏洪亚; 路波; 查俊; 余立; 寇西平

doi:10.13224/j.cnki.jasp.20240126

重气体风洞试验数据修正方法综述

doi: 10.13224/j.cnki.jasp.20240126

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

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: 智强基金；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:
寇西平（1987-），男，副研究员，博士，主要从事飞行器气动弹性力学研究。E-mail：kouxiping@cardc.cc

中图分类号: V211.24
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出版历程
- 收稿日期: 2024-03-04
- 网络出版日期: 2024-10-25

Survey of test data correction method in heavy gas wind tunnel

LIU Yongping^1
,,
XIA Hongya¹,
LU Bo¹,
ZHA Jun¹,
YU Li¹,
KOU Xiping^{1, 2,*
, ,}

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:
全面综述了重气体风洞试验数据修正方法，深入探讨了重气体介质在气动弹性试验中的独特优势及其对气动特性的影响。重气体介质由于其高密度和低声速特性，在设计气动弹性动力学相似风洞模型和开展颤振试验方面具有显著优势。然而，与空气相比，重气体介质的热力学特性差异对气动特性产生显著影响，这要求必须对试验数据进行适当的修正以确保其在空气中的适用性。从理论和试验两个角度出发，对比分析了跨声速相似律和面积相似律两种主要的修正方法，结果表明：跨声速相似律在修正气动特性时更为有效。此外，将跨声速相似原理应用于重气体介质颤振试验数据修正，在刚体二自由度机翼状态下修正效果较好，对于柔性多自由度机翼修正效果差。通过深入分析跨声速相似原理的理论基础，揭示了在特定条件下颤振数据修正方法的局限性。研究结果为重气体介质试验数据的准确修正提供了理论依据。
- 颤振试验 /
- 重气体介质 /
- 热力学特性 /
- 相似律 /
- 试验数据相关性
Abstract:
The data correction methods for heavy gas wind tunnel testing were comprehensively reviewed by thoroughly examining the unique advantages of heavy gas media in aeroelastic experiments and its impact on aerodynamic characteristics. Heavy gas media, due to its high density and low speed of sound, had significant benefits in the design of aeroelastic dynamic similarity wind tunnel models and the flutter tests. However, the thermodynamic property differences from air necessitated appropriate adjustments to the test data to ensure its applicability in air. The transonic similarity law and the area similarity law were compared from both theoretical and experimental perspectives, indicating that the transonic similarity law is more effective in adjusting aerodynamic characteristics. Furthermore, applying the transonic similarity principle to the correction of flutter test data using heavy gas media yielded satisfactory results for rigid two-degree-of-freedom wings but less effective for flexible multi-degree-of-freedom wings. Through an in-depth analysis of the theoretical basis of the transonic similarity principle, the limitations of flutter data correction methods under specific conditions were revealed. This research could provide a theoretical basis for accurate correction of heavy gas media test data.
- flutter test /
- heavy gas medium /
- thermodynamic characteristics /
- similarity rules /
- test data correlation

HTML

图 1 TDT示意图^[10]

Figure 1. Schematic diagram of TDT^[10]

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图 2 相同总温不同总压下γ～Ma曲线（T_t=323 K）

Figure 2. Curves of γ～Ma under same total temperature with different total pressure （T_t=323 K）

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图 3 气动特性的转化^[27]

Figure 3. Transformation of aerodynamic characteristics^[27]

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图 4 NACA0012压力系数比较^[33]（修正前）

Figure 4. Pressure coefficient comparison of NACA0012^[33] （before correction）

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图 5 NACA0012压力系数比较^[33]（修正后）

Figure 5. Pressure coefficient comparison of NACA0012^[33] （after correction）

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图 6 应用跨声速相似律的试验与计算结果^[34]

Figure 6. Experiment and computation results by using transonic similarity law^[34]

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图 7 面积相似律

Figure 7. Area similarity law

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图 8 面积相似律和跨声速相似律的对比

Figure 8. Comparison of area similarity law and transonic similarity law

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图 9 动态缩放率对颤振边界的影响

Figure 9. Effect of dynamic scale ratio on the flutter boundary

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图 10 翼型厚度对跨声速颤振边界的影响^[48]

Figure 10. Effect of wing thickness on the transonic flutter boundary^[48]

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图 11 攻角对跨声速颤振边界的影响^[48]

Figure 11. Effect of angle of attack on the transonic flutter boundary^[48]

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图 12 非定常压力系数分布^[51]

Figure 12. Distribution of unsteady pressure coefficient^[51]

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图 13 颤振边界随翼型厚度变化示意图^[48]

Figure 13. Schematic of flutter boundary in the change of the thickness of the wing^[48]

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图 14 PAPA支撑系统和BSCW^[62]

Figure 14. Support system （PAPA） and BSCW^[62]

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图 15 BSCW颤振数据及跨声速相似律修正

Figure 15. BSCW flutter data and transonic similarity correction

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图 16 柔性机翼颤振边界

Figure 16. Flutter boundary of flexible wing

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表 1 气体特性对比

Table 1. Comparisons of gas characteristics

气体 ρ/（kg/m³ ） a/（m/s） γ

空气 1. 177 347. 32 1. 402

R-134a 4. 23 162. 03 1. 119

SF₆ 6. 0 135. 40 1. 098

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