重气体介质中气动特性的相关性修正

刘永平; 查俊; 胡哲; 寇西平; 余立; 路波

doi:10.13224/j.cnki.jasp.20230748

重气体介质中气动特性的相关性修正

doi: 10.13224/j.cnki.jasp.20230748

刘永平^1,,
查俊^1,*, ,,
胡哲¹,
寇西平^{1, 2},
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: 智强基金项目；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:
查俊（1984-），男，副研究员，硕士，主要从事飞行器气动弹性力学研究。E-mail：june_zhazha@163.com

中图分类号: V211.24
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- 被引次数: 0
出版历程
- 收稿日期: 2023-11-27
- 网络出版日期: 2025-05-13

Correlation correction of aerodynamic characteristics in heavy gas medium

LIU Yongping^1
,,
ZHA Jun^{1,*
, ,},
HU Zhe¹,
KOU Xiping^{1, 2},
YU Li¹,
LU Bo¹

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:
以超临界翼型RAE2822和CHN-T2标模为研究对象，用CFD方法计算了其在重气体介质和空气中的定常跨声速气动特性，基于跨声速相似律和临界比热比将重气体介质中的气动数据转换到等效空气介质下的数据。结果表明：修正后两种介质中物面压力分布吻合性较好，对于颤振试验所关心的小迎角范围内的升力系数曲线和俯仰力矩系数曲线的斜率，经过相似性修正后重气体介质中所得的斜率值与空气介质中的相差不超过2%，满足颤振试验的要求。
- 重气体介质 /
- 气动特性 /
- 跨声速相似律 /
- 相似性转换 /
- 颤振试验
Abstract:
The steady transonic aerodynamic characteristics of supercritical airfoil RAE2822 and CHN-T2 in heavy gas and air were calculated by CFD. Based on the transonic similarity law and critical specific heat ratio, aerodynamic data in heavy gas medium were converted to data in equivalent air medium. The results showed that the surface pressure distributions in these two media were in good agreement with each other. For flutter tests, the slope of the lift coefficient curve and pitch moment coefficient curve at small angles of attack raised concern, after similarity correction, the slope values obtained in heavy gas medium was less than 2% different from that in air medium, which met the requirements of flutter test.
- heavy gas medium /
- aerodynamic characteristics /
- transonic similarity law /
- similarity correction /
- flutter test

HTML

图 1 RAE2822翼型网格

Figure 1. Mesh of airfoil RAE2822

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图 2 CHN-T2标模及表面网格

Figure 2. CHN-T2 standard model and surface mesh

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图 3 RAE2822翼型表面压力系数分布

Figure 3. Pressure coefficient distribution of airfoil RAE2822

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图 4 压力系数分布（修正前）

Figure 4. Pressure coefficient distribution （before correction）

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图 5 压力系数分布（修正后）

Figure 5. Pressure coefficient distribution （after correction）

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图 6 RAE2822的C_L-α曲线

Figure 6. Curves of C_L-α for RAE2822

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图 7 RAE2822的C_m-α曲线

Figure 7. Curves of C_m-α for RAE2822

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图 8 CHN-T2的压力系数云图

Figure 8. Pressure coefficient nephogram of CHN-T2

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图 9 CHN-T2表面压力系数分布

Figure 9. Pressure coefficient distribution of CHN-T2

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图 10 CHN-T2的C_L-α曲线

Figure 10. Curves of C_L-α for CHN-T2

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图 11 CHN-T2的C_m-α曲线

Figure 11. Curves of C_m-α for CHN-T2

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表 1 计算工况

Table 1. Computational operating conditions

气体	比热比	Ma	p₀/Pa	T₀/K	p_∞/Pa	q_∞/Pa	T_∞/K	Re/10⁷
空气	γ=1.4	0.725	330000	302	232581	97419	273.27	4.0
SF₆	$ \gamma ' $=1.07395	0.7444	136436	302	101325	35111	294.26
SF₆	γ^*=1.10049	0.7428	136436	302	101453	34983	294.29
R-134a	γ^*=1.12217	0.7414	136436	302	101321	35115	293.01

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表 2 修正参数

Table 2. Modified parameters

气体	比热比	Ma	A
空气	γ=1.4	0.725	1
SF6	$ \gamma ' $=1.07395	0.7444	0.9693
SF6	γ^*=1.10049	0.7428	0.9723
R-134a	γ^*=1.12217	0.7414	0.9741

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表 3 RAE2822的气动导数

Table 3. Aerodynamic derivative of RAE2822

气体	$C_L^{\mathrm{a}} $/（°）	$\Delta C_L^{\mathrm{a}} $/%	$C_m^{\mathrm{a}} $/（°）	$\Delta C_m^{\mathrm{a}} $/%
空气	0.1906		−0.0492
R-134a修正后	0.1939	5.0	−0.0502	4.9
R-134a修正前	0.2001	1.7	−0.0516	2.0

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表 4 CHN-T2的气动导数

Table 4. Aerodynamic derivative of CHN-T2

气体	$C_L^{\mathrm{a}} $/（°）	$\Delta C_L^{\mathrm{a}} $/%	$C_m^{\mathrm{a}}$/（°）	$\Delta C_m^{\mathrm{a}}$/%
空气	0.1228		−0.4896
R-134a修正后	0.1219	0.7	−0.4867	0.6

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