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层流-湍流的转捩问题是飞行器设计研制面临的重要气动难题. 当飞行马赫数较高时, 飞行器表面同时存在高温气体热化学反应与微孔隙效应, 此时边界层失稳问题更加复杂, 其机理认识尚不清楚. 本文建立了同时考虑高温化学非平衡效应和表面微孔隙效应的线性稳定性分析方法, 并针对高空H = 25 km、马赫数10, 15和20的飞行工况, 对比分析了化学非平衡效应、微孔隙效应以及两种效应共存时对流动稳定性的影响. 研究发现, 化学非平衡效应能够促进边界层模态失稳, 微孔隙效应能够抑制第二模态失稳, 前者作用强于后者, 导致两者共存时整体上促进第二模态失稳. 化学非平衡效应能够降低孔隙效应抑制第二模态对应的频率范围, 造成在局部低频范围内化学非平衡效应可以增强微孔隙效应的抑制效果, 而在高频范围内减弱其抑制效果, 导致孔隙效应N值降低量整体上减小. 此外, 两种效应共存时马赫数变化对微孔隙效应抑制第二模态的能力影响不大.The transition from laminar to turbulent flow is one of the main aerodynamic challenges in aircraft design and development. When the flight Mach number is sufficiently high, the aircraft surface experiences micropore effects and high-temperature gas thermochemical reactions. At present, boundary layer instability has become a more complex problem, and its mechanism is still unclear. In this study, a linear stability analysis method is developed which takes into consideration high-temperature chemical non-equilibrium process and surface micropore effect. For flight conditions at high altitude (H = 25 km) with Mach numbers 10, 15, and 20, the effects of micropore effects, chemical non-equilibrium effects, and their joint effect on flow stability are contrasted and investigated. The results show that the chemical non-equilibrium effect can contribute to the boundary layer's mode instability, while the micropore effect can restrain the second mode instability. The coexistence of the two often contributes to the instability of the second mode, because the former is heavier than the latter. The chemical non-equilibrium effect can reduce the frequency range corresponding to the second mode of pore effect inhibition, which results in the chemical non-equilibrium effect enhancing the inhibition effect of the micropore effect in the local low-frequency range and weakening its inhibition effect in the high-frequency range. This, in turn, causes a decrease in the corresponding N value variation by pore effect. Furthermore, when both effects are present, the micropore effect's capacity to inhibit the second mode is not significantly affected by change in Mach number.
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Keywords:
- boundary layer /
- stability /
- chemical non-equilibrium /
- micropore effect
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图 2 CPG工况流向x/Lref = 600处温度剖面对比
Fig. 2. Temperature profile comparison under CPG circumstance at x/Lref = 600.
图 3 CNE工况流向x/Lref = 600处基本流对比 (a)流向速度; (b)温度; (c)组分浓度
Fig. 3. Baisc flow profiles at x/Lref = 600 under CNE circumstance: (a) Streamwise velocity; (b) temperature; (c) species concentration.
图 4 稳定性分析结果与文献对比 (a)特征函数; (b)模态增长率
Fig. 4. Comparison of literature and present results: (a) Eigenfunction; (b) growth rate.
图 5 网格无关性验证 (a)流向速度; (b)模态增长率
Fig. 5. Verification of grid independence: (a) Streamwise velocity; (b) growth rate.
图 6 CPG下Ma10工况在位置x/Lref = 400模态增长率对比
Fig. 6. Comparison of growth rate at position x/Lref = 400 for Ma10 condition under CPG.
图 7 微槽和圆孔的对比 (a) N值曲线; (b) 模态增长率变化率
Fig. 7. Comparison of results between microgrooves and micropores: (a) N-value curves; (b) relative change of growth rate.
图 8 不同截面参数下在位置x/Lref = 600的模态增长率变化
Fig. 8. Changes in growth rate under different cross-sectional parameters at x/Lref = 600.
图 9 Ma10工况不同气体模型边界层基本流剖面 (a)速度; (b)温度
Fig. 9. Basic flow profiles of boundary layer for different gas models under Ma10 condition: (a) Streamwise velocity; (b) temperature.
图 10 Ma10工况不同气体模型模态增长率和相速度对比 (a) x/Lref = 600; (b)沿流向F = 124 kHz
Fig. 10. Comparison of growth rate and phase velocity of different gas models under Ma10: (a) x/Lref = 600; (b) modal frequency F = 124 kHz along the streamwise direction.
图 11 Ma10工况不同气体模型对比 (a)中性曲线; (b)N值包络
Fig. 11. Comparison of different gas model under Ma10: (a) Neutral curve; (b) N-value envelope.
图 12 不同气体模型光滑和多孔壁增长率及其相对变化率对比 (a) x/Lref = 400; (b) x/Lref = 600; (c) x/Lref = 800
Fig. 12. Comparing the growth rates of smooth and porous walls and their relative change for different gas models: (a) x/Lref = 400; (b) x/Lref = 600; (c) x/Lref = 800.
图 13 光滑和多孔壁在x/Lref = 600处压力特征函数对比
Fig. 13. Comparison of the pressure eigenfunctions at x/Lref = 600 for smooth and porous walls.
图 14 不同气体模型光滑与多孔壁的N值包络线对比
Fig. 14. Comparison of N-value envelope for smooth and porous walls of different gas models.
图 15 CNE工况不同马赫数的模态增长率对比 (a) x/Lref = 600; (b) 沿流向F = 130 kHz
Fig. 15. Comparison of growth rates at different Mach numbers under CNE condition: (a) x/Lref = 600; (b) modal frequency F = 130 kHz along the streamwise direction
图 16 不同马赫数中性曲线对比 (a) CPG; (b) CNE
Fig. 16. Comparison of neutral curves at different Mach numbers: (a) CPG; (b) CNE.
图 17 CNE工况不同马赫数N值包络对比
Fig. 17. Comparison of N-value envelopes at different Mach numbers under CNE condition.
图 18 不同马赫数光滑和多孔壁增长率及相对变化率对比 (a) x/Lref = 400; (b) x/Lref = 600
Fig. 18. Comparison of growth rates and relative change of smooth and porous walls at different Mach numbers: (a) x/Lref = 400; (b) x/Lref = 600.
图 19 不同马赫数下光滑与多孔壁的N值包络
Fig. 19. N-value envelopes of smooth and porous walls at different Mach numbers.
表 1 不同马赫数对应来流参数
Table 1. Flow characteristics for various Mach numbers.
Ma Te/K ρe/(kg·m–3) Ue/(m·s–1) Re/m–1 10 221.55 0.040085 2983.6 8.26×106 15 221.55 0.040085 4475.4 1.24×107 20 221.55 0.040085 5967.2 1.65×107 
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表 3 不同马赫数下x/Lref=900位置的N值相对变化率
Table 3. Relative change of N-values at x/Lref=900 under different Mach numbers.
Ma (ΔN/Nmax, smooth) CPG (ΔN/Nmax, smooth) CNE 10 26.8% 18.2% 15 22.1% 19.8% 20 27.2% 15.5%
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