Mechanism Analysis of Start and Unstart Flow Characteristic Structures of a Supersonic Inlet
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摘要: 基于Wagner等实验的超声速进气道模型, 采用RANS-SST计算方法分析超声速进气道起动和不起动流场特性。通过拓宽计算域和采用来流边界层自由发展方法, 准确预测了典型的进气道不起动过程中可能出现的周期性振荡流现象, 包括进气道内部高压的产生和降低、下壁面大尺度分离泡的膨胀收缩和迁移, 并伴随不起动激波的传播。进气道完全起动状态(末端活门挡板角度β=0°)时得到的波系结构、壁面压强和流向速度分布计算结果与实验测量值相吻合; 不起动状态(β=28°)时流场的振荡周期和振幅与实验结果一致。对进气道不起动的非定常流场进行动态模态分解, 发现了3个特征频率: 主频f1=69.8 Hz的流场模态揭示了进气道出口的压强振荡最强, 而入口及上壁面的速度振荡最强; 二倍频f2=139.7 Hz和三倍频f3=209.5 Hz捕捉到的流场模态主要是离散的小尺度高能结构。在不起动状态的振荡过程中, 进气道入口外部流场产生了较大的速度和压力脉动, 所以对进气道内外流场相互作用的准确描述是预测不起动状态振荡流动的重要因素。Abstract: Based on the supersonic inlet model in Wagner's experiment, RANS-SST was used in numerical simulation to analyze the inlet start and unstart flow field characteristics. By broadening the computational domain and adopting the free development method of boundary layer, the possible periodic oscillatory flow phenomena in the process of the inlet unstart, such as the high-pressure generation and reduction inside the inlet, the expansion and contraction of large-scale separation bubbles at the lower wall, and the unstart shock propagation, were accurately predicted. For inlet start at the flap angle of 0, the wave structures, wall pressure, and flow velocity distributions were consistent with the existing experimental results. For inlet unstart at the flap angle of 28, the oscillation period and amplitude of the flow field were in agreement with the experimental data. The dynamic mode decomposition of the unsteady flow of the inlet unstart was carried out. In the flow field mode with the main frequency f1=69.8 Hz, the pressure oscillation at the outlet of the inlet is the strongest, while the velocity oscillation at the inlet and the upper wall is the strongest. In addition, the flow field modes captured by double frequency f2=139.7 Hz and triple frequency f3=209.5 Hz are mainly discrete small-scale high-energy structures. In the oscillation process of the inlet unstart, the flow field outside the inlet produces large velocity and pressure pulsation. Therefore, the accurate description of the interaction between the fields inside and outside the inlet is an important factor to predict the inlet unstart oscillatory flow.
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Key words:
- inlet /
- unstart /
- oscillatory flow /
- shock wave /
- dynamic mode decomposition
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图 3 不同网格的壁面压强分布曲线
Figure 3. Wall pressure distribution curves under different grid resolutions
图 5 进气道对称面纹影图和压强分布
Figure 5. Schlieren diagram and pressure contours at symmetry plane of the inlet
图 6 激波和湍流边界层相互作用流场结构
Figure 6. Flow field structure of interaction between shock waves and turbulent boundary layer
图 10 进气道在不同β下的平均压强分布
Figure 10. Average pressure contours of the inlet at different angles of β
图 11 不同β下壁面平均压强分布曲线
Figure 11. Average wall pressure distribution curves at different angles of β
图 13 β=25°的进气道对称面压强分布随时间的变化
Figure 13. Time history of pressure distribution on the symmetry plane of the inlet at β=25°
图 14 β=25°的进气道对称面流线随时间的变化
Figure 14. Time history of streamlines on the symmetry plane of the inlet at β=25°
图 16 频率f1对应DMD模态的幅值和相位(压力场)
Figure 16. Amplitude and phase of DMD mode at frequency f1(pressure field)
图 17 频率f1对应DMD模态的幅值和相位(速度场)
Figure 17. Amplitude and phase of DMD mode at frequency f1 for velocity
图 18 f2，f3对应DMD模态的幅值(压力场)
Figure 18. Amplitudes of DMD modes at frequencies f2 and f3(pressure field)
Tt/K Pt/MPa Ma V/(m/s) 330 2.5 4.9 740 
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表 2 网格参数
Table 2. Grid parameters
case total elements initial layer thickness/mm grid 1 5.94×105 0.08 grid 2 9.86×105 0.08 grid 3 1.469×106 0.05 grid 4 2.243×106 0.05
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表 3 不起动激波的平均传播速度
Table 3. Average propagation speed of unstart shock
β/(°) shock speed/(m/s) oscillatory period/ms oscillatory frequency/Hz 25 79.01 14.5 68.96 28 92.15 9.5 105.26
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