Analysis of non-equilibrium effect in hypersonic vehicle’s jet interaction flow field
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摘要:
针对高超声速飞行器绕流与反作用控制系统（RCS）喷流相互干扰过程中高温气体非平衡效应的影响问题，基于高温空气及喷流燃气物理化学模型，通过数值求解三维非平衡雷诺平均Navier-Stokes（RANS）方程，开展了典型外形喷流干扰非平衡流场的数值模拟，研究了绕流空气非平衡效应、喷流燃气非平衡效应及其综合的流场高温非平衡效应的影响，分析了不同飞行条件下流场高温气体非平衡效应对流场结构及飞行器气动力热特性影响的变化规律。研究表明：绕流空气非平衡效应在高马赫数下影响显著，表现为减小喷流附加推力、降低干扰区热流峰值，随着马赫数升高，其影响逐渐增大；喷流燃气非平衡效应在不同状态下的影响存在差别，在低空状态下，燃气组分主要发生复燃/复合反应，导致喷流附加推力增大、干扰区热流峰值升高，在高空状态下，燃气组分主要发生离解反应，导致喷流附加推力减小、干扰区热流峰值降低，沿弹道高度升高，喷流燃气的复合反应减弱而离解反应增强；为了更加真实地模拟高超声速飞行器RCS喷流干扰流场特性，有必要全面地考虑流场中的高温气体非平衡效应。
Abstract:The non-equilibrium effect of high temperature gas in hypersonic vehicle reaction control system’s (RCS) jet interaction flow field was studied. Based on high temperature air and jet gas’s physical and chemical reaction model and by solving three-dimensional non-equilibrium Reynolds-averaged Navier-Stokes (RANS) equations, numerical simulation of typical configuration’s jet interaction non-equilibrium flow field was conducted, the influences of air and jet gas’s non-equilibrium effect were analyzed, and the influences under various flight conditions were also discussed. The results showed that: air’s non-equilibrium effect was significant when flight Mach number was high, which can reduce the additional thrust produced by jet interaction, and decrease the heat flux in jet interaction area; high flight velocity could enhance this effect. Jet gas’s non-equilibrium effect varied under different conditions; when flight altitude was low, jet gas’s components mainly involved in afterburning/recombination reactions, which can increase additional thrust and the heat flux in jet interaction area; when flight altitude was high, jet gas’s components mainly involved in dissociation reactions, which can decrease additional thrust and the heat flux; as the flight altitude increased through the trajectory, jet gas’s dissociation reactions were enhanced and recombination reactions were weakened. To simulate hypersonic vehicle’s jet interaction flow field more precisely, it is necessary to consider high temperature gas non-equilibrium effect.
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图 3 模型表面压力计算与文献和试验结果对比（α=20°）
Figure 3. Comparison of surface pressure distribution between present CFD result and reference experiment result （α=20°）
图 9 绕流空气非平衡效应对激波结构的影响（α=0°）
Figure 9. Influence of air nonequilibrium effect on shock structure （α=0°）
图 10 绕流空气非平衡效应对表面压力分布的影响
Figure 10. Influence of air nonequilibrium effect on surface pressure distribution
图 11 绕流空气非平衡效应对表面热流分布的影响
Figure 11. Influence of air nonequilibrium effect on surface heat flux distribution
图 12 绕流空气非平衡效应对推力放大因子的影响
Figure 12. Influence of air nonequilibrium effect on thrust amplification factor
图 13 绕流空气非平衡效应对干扰区热流峰值的影响
Figure 13. Influence of air nonequilibrium effect on surface maximum heat flux value
图 14 上表面对称线上的组分质量分数分布对比
Figure 14. Comparison of species mass fraction distribution along upper side symmetric line
图 15 燃气非平衡效应对激波结构的影响（α=0°）
Figure 15. Influence of jet gas’s nonequilibrium effect on shock structure （α=0°）
图 17 喷流燃气非平衡效应对表面压力分布的影响
Figure 17. Influence of jet gas nonequilibrium effect on surface pressure distribution
图 18 喷流燃气非平衡效应对表面热流分布的影响
Figure 18. Influence of jet gas nonequilibrium effect on surface heat flux distribution
图 19 喷流燃气非平衡效应对推力放大因子对比的影响
Figure 19. Influence of jet gas nonequilibrium effect on thrust amplification factor
图 20 喷流燃气非平衡效应对干扰区热流峰值的影响
Figure 20. Influence of jet gas nonequilibrium effect on surface maximum heat flux value
图 21 流场高温非平衡效应对推力放大因子的影响
Figure 21. Influence of flow field high temperature nonequilibrium effect on thrust amplification factor
图 22 流场高温非平衡效应对干扰区热流峰值的影响
Figure 22. Influence of flow field high temperature nonequilibrium effect on surface maximum heat flux value
表 1 高温空气化学反应模型
Table 1. Chemical reaction model of air
编号 反应式 编号 反应式 1 N2+M1 ↔N+N+M1 4 O+NO ↔N+O2 2 O2+M2 ↔O+O+M2 5 O+N2 ↔N+NO 3 NO+M3 ↔N+O+M3 6 N+O ↔NO++e 
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表 2 喷流燃气组分化学反应模型
Table 2. Chemical reaction model of jet gas components
编号 反应式 编号 反应式 1 CO2+M4 ↔CO+O+M4 7 OH+CO ↔CO2+H 2 CO2+O ↔ O2+CO 8 OH+H2 ↔H2O+H 3 CO+NO ↔ CO2+N 9 H+O2 ↔OH+O 4 H2O+M5 ↔H+OH+M5 10 O+H2 ↔OH+H 5 H2+M6 ↔H+H+M6 11 OH+OH ↔H2O+O 6 OH+M7 ↔O+H+M7
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表 3 推力放大因子对比
Table 3. Comparison of thrust amplification factor
攻角/（°） 推力放大因子 误差/% 试验 CFD 0 1.367 1.372 0.37 20 1.438 1.424 0.97 40 1.375 1.331 3.2
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表 4 不同网格计算得到的气动力系数对比
Table 4. Comparison of aerodynamic characteristics computed by different grids
参数 稀网格 中等加密网格 密网格 Ca 0.1478 0.1480 0.1479 Cn −0.0158 −0.0159 −0.0159 Cmz −0.0175 −0.0176 −0.0176
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表 5 计算状态
Table 5. Computation conditions
编号 H/km Ma∞ α/（°） 1 20 5 0 2 30 8 0 3 40 10 0 4 50 15 0 5 60 20 0 6 70 25 0
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表 6 来流空气非平衡效应引起的气动力特性变化
Table 6. Variation of aerodynamic characteristics caused by inflow air’s non-equilibrium effect
参数 空气非平衡流模型 完全气体异质流模型 Ca 0.1464 0.1428 Cn −0.0818 −0.1180 Cmz −0.0101 −0.0155 K 1.0146 1.0211 ${F_{ {\text{n} },{\rm{ji} } } }$/N −99.55 −143.60 ${M}_{{\rm{ji}}}$/（N·m） −12.29 −18.87
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表 7 喷流燃气非平衡效应引起的气动力特性变化
Table 7. Variation of aerodynamic characteristics caused by jet gas’s non-equilibrium effect
参数 H=60 km H=20 km 燃气/空气混合反应流 燃气冻结流 燃气/空气混合反应流 燃气冻结流 Ca 0.1460 0.1464 0.1480 0.1482 Cn −0.0692 −0.0810 −0.0159 −0.0047 Cmz −0.0071 −0.0104 −0.0176 −0.0226 K 1.0124 1.0145 1.0448 1.0132 ${F_{{\rm{n}},{\rm{ji} } } }$/N −84.26 −98.54 −304.61 −89.80 ${M_{{\rm{ji}}} }$/（N·m） −8.60 −12.70 −337.70 −433.89
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