Geometric-flow synergistic design for low-Mach-number self-starting inward turning inlet
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摘要:
为解决高超声速内收缩进气道低马赫数自起动困难及隔离段内涡流区显著的问题，提出了一种基于几何结构与流动控制的协同设计方法。该方法将“侧板分割-前掠-外移”的几何重构与受控侧向溢流策略相结合，显著降低了进气道有效内收缩比，并实现了对分离流和附面层的协同抑制与排除。三维数值计算结果表明：与常规唇口后切方案相比，新型进气道宽马赫数范围内的性能显著提升：自起动马赫数由3.9降至3.2，起动马赫数由3.3降至3.1；在来流马赫数为4.0和6.0工况下，实际捕获流量分别提高9.74%和6.54%，出口总压恢复系数分别提高9.91%和4.45%。此外，出口畸变指数显著降低（≥13%），并且在来流马赫数为4.0时出口截面的涡流区基本消失。
Abstract:A synergistic design method combining geometric configuration and flow control was proposed to enhance the low-Mach-number self-starting capability and mitigate vortex region in hypersonic inward-turning inlets. The method combined geometric reconstruction of “side wall segmentation, forward sweep, and outward translation” with a controlled side overflow strategy, significantly reducing the effective internal contraction ratio and achieving coordinated suppression and removal of separated flow and boundary layer. Three-dimensional numerical results show that, compared with the conventional rear-cut-lip configuration, the novel inlet achieves significant performance improvements over a wide Mach number range. The self-starting Mach number decreases from 3.9 to 3.2 and the starting Mach number decreases from 3.3 to 3.1. When the inflow Mach number is 4.0 and 6.0, the actual captured mass flow increases by 9.74% and 6.54%, respectively, and the exit total pressure recovery coefficient increases by 9.91% and 4.45%. Additionally, the exit distortion index is reduced by at least 13%, and at an inflow Mach number of 4.0, the vortex region is essentially eliminated.
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Key words:
- hypersonic /
- inward turning inlet /
- starting performance /
- flow control /
- wide Mach number adaptability
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图 1 设计点时激波配置和马赫数分布双控基准流场结构（Ma∞=6.0）
Figure 1. Basic flowfield structure with dual control of shock configuration and Mach number distribution at design point （Ma∞=6.0）
图 2 接力点时激波配置和马赫数分布双控基准流场结构（Ma∞=4.0）
Figure 2. Basic flowfield structure with dual control of shock configuration and Mach number distribution at the relay point （Ma∞=4.0）
图 3 基准进气道的进口截面及气动构型
Figure 3. Intake section and aerodynamic configuration of the reference inlet
图 7 进气道壁面沿程静压分布数值结果与实验数据对比（Ma∞=6.0）
Figure 7. Comparison of numerical and experimental static pressure distributions along the wall （Ma∞=6.0）
图 8 不同来流马赫数时Inlet 1对称面、喉道和出口截面马赫数等值线图
Figure 8. Mach number contours on the symmetry plane, throat, and exit sections of Inlet 1 at various Mach number
图 9 不同来流马赫数时Inlet 1沿程横截面流场
Figure 9. Cross-sectional flow fields along flow path of Inlet 1 at various Mach number
图 11 Inlet 1不起动流场的分离包形态
Figure 11. Separation-bubble morphology in the unstarted flow field of Inlet 1
图 14 进气道侧板分割设计示意图（侧视图）
Figure 14. Design schematic of sidewall-splitting for the inlet（side view）
图 16 基准进气道V型唇口点横截面速度分布
Figure 16. Cross-sectional velocity distribution at the V-shaped lip point of the reference inlet
图 18 不同来流马赫数时Inlet 2对称面、喉道及出口截面马赫数等值线图
Figure 18. Mach number contours on the symmetry plane, throat, and exit sections of Inlet 2 at various Mach number
图 19 不同来流马赫数时Inlet 2沿程横截面流场
Figure 19. Cross-sectional flow fields along flow path of Inlet 2 at various Mach number
图 21 Ma∞=3.0时Inlet 2不起动流场中的分离包形态
Figure 21. Separation-bubble morphology in the unstarted flow field of Inlet 2 at Ma∞= 3.0
图 22 Ma∞=3.1时Inlet 2的起动流场波系结构
Figure 22. Shock-system structure of the starting flow field in Inlet 2 at Ma∞=3.1
表 1 不同马赫数下的来流参数
Table 1. Freestream parameters at different Mach number
Ma∞ H/km p∞/Pa T∞/K 4.0 17 8850 216.6 5.0 21 4729 217.6 6.0 25 2549 221.6 7.0 29 1390 225.5 
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表 2 不同网格密度下Inlet 1的出口性能参数
Table 2. Exit performance parameters of Inlet 1 under different grid densities
网格密度 σe pe/p0 粗网格 0.532 20.21 中等网格 0.539 20.11 细网格 0.539 20.13
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表 3 不同来流马赫数下两种进气道总体性能参数
Table 3. Overall performance parameters of the inlets at various Mach number
进气道 Ma∞ φth φb qm/（kg/s） σth pth/p∞ Math σe pe/p∞ Mae εe Dt/N Inlet 1 4.0 0.651 3.90 0.828 11.3 2.19 0.696 12.9 1.97 1.47 807 5.0 0.762 3.04 0.790 14.0 2.82 0.625 15.7 2.55 1.76 597 6.0 0.841 2.14 0.735 17.5 3.36 0.539 20.1 2.97 2.34 507 7.0 0.896 1.44 0.666 21.3 3.85 0.442 25.7 3.30 2.94 352 Inlet 2 4.0 0.657 0.203 4.28 0.892 11.7 2.25 0.765 13.0 2.06 1.21 1043 5.0 0.766 0.186 3.34 0.839 13.9 2.89 0.694 16.0 2.63 1.52 711 6.0 0.811 0.187 2.28 0.773 16.6 3.46 0.563 20.0 3.06 2.03 491 7.0 0.825 0.175 1.46 0.694 19.5 3.99 0.428 23.2 3.43 2.47 351
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表 4 进气道起动马赫数和自起动马赫数
Table 4. Starting and self-starting Mach number of the inlets
进气道 Mas Mars Inlet 1 3.3 3.9 Inlet 2 3.1 3.2
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