超/高超声速流中热喷效应的影响差异分析

孙瑞斌

doi:10.13224/j.cnki.jasp.20240645

超/高超声速流中热喷效应的影响差异分析

doi: 10.13224/j.cnki.jasp.20240645

孙瑞斌

中国航天空气动力技术研究院，北京 100074

详细信息

作者简介:
孙瑞斌（1990-），男，工程师，博士，主要从事喷流控制与复杂流动等方面的研究。E-mail：sunruibin6263@163.com

中图分类号: V211.751
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出版历程
- 收稿日期: 2024-09-17
- 网络出版日期: 2025-01-11

Analysis of differential influence of hot jet effect in supersonic and hypersonic flow

SUN Ruibin

China Academy of Aerospace Aerodynamics，Beijing 100074，China

摘要

摘要:
针对不同来流条件下热喷效应导致的冷/热喷差异规律不同的问题，通过求解三维多组元雷诺平均Navier-Stokes（RANS）方程数值模拟典型飞行器外形轨控喷流干扰流场，研究了喷流温度对干扰流场及气动特性的影响规律，分析了不同来流马赫数与飞行高度条件的冷/热喷干扰差异规律。研究表明：喷流温度对干扰流场的影响是质量流量与能量流量的耦合影响机制，总焓比高于1时，喷流能量流量的影响较质量流量更明显，总焓比低于1时，喷流质量流量的影响较能量流量更明显；随着来流马赫数增加，总焓比下降，喷流质量流量的影响较能量流量增强，质量流量大的冷喷干扰流场范围逐渐大于热喷，并使得冷喷干扰产生的力干扰因子逐渐大于热喷；随着飞行高度增加，总焓比不变，喷流质量流量与能量流量的影响占比不变，冷/热喷干扰差异的定性规律不变，但来流动压减小，喷流干扰力/力矩整体为减小趋势，并使得冷/热喷干扰的力干扰因子与轨控偏移量差异整体为减小趋势。
- 超/高超声速流 /
- 反作用控制系统（RCS） /
- 热喷效应 /
- 分离流动 /
- 气动干扰
Abstract:
In response to the issue of different cold/hot jet differences caused by the hot jet effect under various incoming flow conditions, the numerical investigation of jet temperature effects on the interaction flow field and aerodynamic characteristics was studied by solving the three-dimensional multi-component Reynolds-averaged Navier-Stokes (RANS) equations to simulate the typical aircraft configuration's divert jet interaction flow field. The differences in cold/hot jet interaction under various incoming Mach numbers and flight altitude conditions were analyzed. The study showed that the impact of jet temperature on the interaction flow field exhibited a coupled influence mechanism of mass and energy fluxes. When the total enthalpy ratio was higher than 1, the influence of jet energy flux was more significant than the mass flux. Conversely, when the total enthalpy ratio was lower than 1, the influence of jet mass flux was more significant than the energy flux. As the incoming Mach number increased, the total enthalpy ratio decreased, and the influence of jet mass flux became more pronounced than that of energy flux, and the interaction flow field range of cold jets with large mass flux gradually exceeded that of hot jets, and the force interaction factor caused by cold jets gradually exceeded that of hot jets. As the flight altitude increased, the total enthalpy ratio was constant, and the proportional contribution of jet mass flux and energy flux kept unchanged, the qualitative rule of cold/hot jet interaction differences remained unchanged, but the reduction in incoming dynamic pressure resulted in an overall decreasing trend of the jet interaction force and moment, it also led to an overall decreasing trend in the difference between the force interaction factor and the shift amount of jet force center of cold and hot jets interaction.
- supersonic and hypersonic flows /
- reaction control system (RCS) /
- hot jet effect /
- separation flow /
- aerodynamic interaction

HTML

图 1 实验锥-柱-裙模型^[33-34]

Figure 1. Cone-cylinder-flare of experiment^[33-34]

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图 2 壁面子午线压力系数分布

Figure 2. Pressure coefficient distribution at wall meridian

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图 3 锥-柱-裙的配置

Figure 3. Configuration of cone-cylinder-flare

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图 4 计算网格

Figure 4. Computation grid

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图 5 不同网格模拟的压力分布对比

Figure 5. Comparison of pressure distribution with different grid simulations

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图 6 干扰流场结构

Figure 6. Structure of interaction flow field

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图 7 壁面压力分布

Figure 7. Pressure distribution of wall

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图 8 喷流干扰随总焓比的变化规律

Figure 8. Variation pattern of jet interaction with the change of total enthalpy ratio

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图 9 不同来流马赫数的分离距离与峰值压力

Figure 9. Separation distance and peak pressure with different Mach numbers

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图 10 不同来流马赫数的力干扰因子与轨控偏移量

Figure 10. Force interaction factor and shift amount of jet force center with different Mach numbers

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图 11 不同来流马赫数0°子午线压力分布

Figure 11. Pressure distribution of 0° meridian with different Mach numbers

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图 12 不同飞行高度的分离距离与峰值压力

Figure 12. Separation distance and peak pressure with different flight altitudes

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图 13 不同飞行高度的力干扰因子与轨控偏移量

Figure 13. Force interaction factor and the shift amount of jet force center with different flight altitudes

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图 14 不同飞行高度0°子午线压力分布

Figure 14. Pressure distribution of 0° meridian with different fly heights

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图 15 冷/热喷流干扰的壁面压力云图及极限流线

Figure 15. Wall pressure contour and limit streamline of cold jet and hot jet interaction

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图 16 冷/热喷流干扰的0°子午线压力分布对比

Figure 16. Comparison of 0° meridian pressure distribution of cold jet and hot jet interaction

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图 17 不同来流马赫数下冷/热喷干扰气动特性对比

Figure 17. Comparison of aerodynamics characteristics of hot jet and cold jet interaction with different Mach numbers

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图 18 不同飞行高度下的冷/热喷干扰气动特性对比

Figure 18. Comparison of aerodynamics characteristics of hot jet and cold jet interaction with different fly altitudes

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表 1 实验喷流条件^[33-34]

Table 1. Jet parameters of experiment^[33-34]

喷流	Ma_j	p_0j/MPa	T_0j/K	γ_j	R_j/（J/（kg·K））
热喷	1.0	12	2300	1.235	319
冷喷	1.0	12	293	1.4	287

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表 2 喷流条件

Table 2. Jet parameters

喷流	p_j/kPa	φ_j/ kPa	T_0j/K	γ_j	R_j/（J/（kg· K））
热喷	133.3	5.01	3200	1.257	400
冷喷	133.3	5.01	293	1.4	287

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表 3 不同网格气动力/力矩计算结果

Table 3. Aerodynamic results of different grids

网格	F_x/N	F_y/N	M_z/（N·m）
1	1352.32	−164.77	67.29
2	1358.44	−169.15	70.04
3	1361.66	−170.25	76.58
4	1361.64	−170.11	77.15

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表 4 不同总温喷流干扰流场相似参数

Table 4. Similarity parameters of interaction flow field with different total temperatures jet

T_0j/K	$ {{{{\dot m}_{\text{j}}}} / {{{\dot m}_\infty }}} $	$ {{{h_{0{\text{j}}}}} / {{h_{0\infty }}}} $	$ {\dot E_{\text{j}}}/{\dot E_\infty } $
400	0.369	0.599	0.221
800	0.261	1.199	0.313
1300	0.205	1.948	0.399
1600	0.185	2.397	0.442
2400	0.151	3.596	0.542
3200	0.130	4.795	0.625

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表 5 不同马赫数条件的总焓比

Table 5. Total enthalpy ratio under different Mach number conditions

T_0j/K	Ma_∞=3	Ma_∞=5	Ma_∞=7
400	1.284	0.599	0.333
800	2.569	1.199	0.666
1300	4.174	1.948	1.082
1600	5.137	2.397	1.332
2400	7.706	3.596	1.998
3200	10.27	4.795	2.664

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表 6 冷/热喷流干扰流场相似参数

Table 6. Similarity parameters of cold jet and hot jet interaction flow field

Ma_∞	$ {{{{\dot m}_{\text{j}}}}/{{{\dot m}_\infty }}} $		$ {{{h_{0{\text{j}}}}}/{{h_{0\infty }}}} $		$ {\dot E_{\text{j}}}/{\dot E_\infty } $
Ma_∞	热喷	冷喷	热喷	冷喷	热喷	冷喷
3	0.217	0.928	10.27	0.483	2.233	0.448
4	0.163	0.696	6.849	0.322	1.117	0.224
5	0.130	0.557	4.795	0.225	0.625	0.126
6	0.109	0.464	3.508	0.165	0.381	0.077
7	0.093	0.398	2.664	0.125	0.248	0.050
8	0.082	0.348	2.084	0.098	0.170	0.034

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