Flow field control method for triangular inclined cut entrance S-shaped inlet under ground state
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摘要:
针对三角形斜切口面S弯进气道地面工作状态，提出了一种基于唇口自给式射流的流场控制方法。通过数值仿真研究表明：唇口自给式射流使进气道口面旋涡被分割成两小一大3个旋涡结构，对称面附近三维分离涡尺度明显减小，对称面附近大尺度旋涡在上壁面的脱落得到延缓，改善了进气道出口截面低总压区分布的周向均匀性，进气道出口截面畸变指数大幅降低。同时，进一步探究了射流缝横向间距、射流缝横向位置、射流角度和射流面积对进气道内部流场结构和气动性能的影响，并得到较优参数配置。相比于基准方案，优选控制方案的总压恢复系数减小甚微，但周向畸变指数
δ 60从0.8164 大幅降低至0.2880 ，满足进气道/发动机匹配要求。Abstract:The internal flow field of a stealthy inlet with an inclined-cut entrance under the ground state exhibited complex three-dimensional separation structures, which greatly reduced the aerodynamic performance of the inlet and cannot meet the requirements of inlet/engine matching. A lip self-supplying air-jet for flow control method of the ground state of a triangular inclined cut entrance inlet was proposed. Numerical simulation results showed that, at the ground state, the original vortex on the entrance of the triangular inclined cut entrance inlet was divided into two small and one large vortices by the lip self-supplying air-jet, the scale of the vortex near the symmetry plane was significantly reduced, and the shedding of the large-scale vortex near the symmetry plane on the upper wall was delayed, improving the circumferential uniformity of the low total pressure area distribution at the exit section of the inlet, and greatly reducing the distortion index. Furthermore, the effects of the transverse spacing of the jet slot, transverse position of the jet slot, jet angle, and jet area on the aerodynamic performance and flow field structure of the stealth inlet under ground state were studied, and the optimal parameter configuration was obtained. Compared with the baseline, the total pressure recovery coefficient of the control method decreased slightly, and the circumferential distortion index
δ 60 significantly dropped from0.8164 to0.2880 , meeting the requirements for inlet/engine matching. -
图 1 基准进气道三角形斜切口面示意图
Figure 1. Schematic diagram of the triangular inclined cut entrance of the baseline inlet
图 4 仿真结果与实验结果S弯进气道出口总压恢复系数分布对比
Figure 4. Comparison of the total pressure recovery coefficient distribution at the S-shaped inlet exit between simulation results and experimental results
图 6 三角形斜切口面进气道地面状态下口面流线图和壁面压力分布云图
Figure 6. Streamlines and wall pressure distribution contours of triangular inclined cut entrance inlet under ground state
图 8 基准方案和控制方案口面流线对比图
Figure 8. Streamlines comparison between the baseline and control methods
图 9 进气道沿中心线不同站位总压恢复系数云图
Figure 9. Contour of total pressure recovery coefficient at different stations along inlet center line
图 10 射流缝不同横向间距ΔY控制方案造型图
Figure 10. Schematic diagram of different transverse spacing of the jet slot ΔY
图 11 射流缝不同横向间距ΔY进气道气动性能对比
Figure 11. Aerodynamic performance comparison of different transverse spacing of the jet slot ΔY
图 12 射流缝不同横向间距ΔY进气道口面流线图
Figure 12. Inlet entrance streamlines of different transverse spacing of the jet slot ΔY
图 13 射流缝不同横向间距ΔY进气道沿中心线不同站位总压恢复系数云图
Figure 13. Contour of total pressure recovery coefficient with different transverse spacing of the jet slot ΔY at different stations along inlet center line
图 14 不同射流缝1横向位置Y进气道控制方案造型图
Figure 14. Schematic diagram of different transverse position of the jet slot one Y
图 15 不同射流缝1横向位置Y进气道气动性能对比
Figure 15. Aerodynamic performance comparison of different transverse position of the jet slot one Y
图 16 不同射流缝1横向位置Y进气道控制方案口面流线图
Figure 16. Entrance streamlines of different transverse position of the jet slot one Y of control method
图 17 射流缝1不同横向位置Y进气道沿中心线不同站位总压恢复系数云图
Figure 17. Contour of total pressure recovery coefficient with different transverse position of the slot one Y at different stations along inlet center line
图 19 不同射流角θ进气道气动性能对比
Figure 19. Inlet aerodynamic performance comparison of different jet angle θ
图 20 不同射流角θ进气道口面流线图
Figure 20. Streamlines of inlet entrance with different jet angle θ
图 21 不同射流角θ进气道沿中心线不同站位总压恢复系数分布云图
Figure 21. Contour of total pressure recovery coefficient with different jet angle θ at different stations along inlet center line
图 22 不同射流面积比γab控制方案造型图
Figure 22. Schematic diagram of control method with different jet area ratios γab
图 23 不同射流面积比γab进气道气动性能对比
Figure 23. Inlet aerodynamic performance comparison of different jet area ratios γab
图 24 不同射流面积比γab进气道口面流线图
Figure 24. Streamlines of inlet entrance of different jet area ratios γab
图 25 不同射流面积比γab进气道沿中心线不同站位总压恢复系数分布云图
Figure 25. Contour of total pressure recovery coefficient with different jet area ratios γab at different stations along inlet center line
D 进气道出口直径 σ 总压恢复系数 ψ 唇缘与轴向夹角 δ60 周向畸变指数 ΔZ 内通道偏距 $\overline {\Delta {\sigma _0}} $ 稳态周向畸变指数 L1 喉道至飞行器前缘距离 ΔY 射流缝横向间距 L2 内通道长度 Y 射流缝1横向位置 γad 进气道面积扩张比 θ 射流角 Ma2 出口截面马赫数 γab 射流面积比 
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表 1 进气道设计参数
Table 1. Inlet design parameters
设计参数 数值 D/mm 624 L1 3.36D L2 4D ΔZ 0.686D 面积扩张比γad 1.3 面积变化规律 缓急相当
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表 2 S弯进气道仿真与实验性能参数对比
Table 2. Comparison of simulation and experimental performance parameters of S-shaped inlet
性能
参数网格数/106 实验 2.4 3.4 4.4 5.4 Ma2 0.44 0.44 0.44 0.44 0.44 σ 0.9742 0.9715 0.9764 0.9762 0.9714 δ60 0.2983 0.3204 0.2747 0.2774 0.2992
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表 3 蛇形进气道仿真与实验性能参数对比
Table 3. Comparison of simulation and experimental performance parameters of serpentine inlet
参数 仿真 实验[9] 总压恢复系数σ 0.952 0.958 稳态周向畸变指数$ \overline {\Delta {\sigma _0}} $/% 11.5 11.7
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表 4 地面状态下基准方案和控制方案气动性能对比
Table 4. Aerodynamic performance comparison between baseline and control methods under ground state
方案 Ma2 σ δ60 控制方案 0.4953 0.8869 0.3608 基准方案 0.5022 0.8894 0.8164
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表 5 射流缝横向间距ΔY对进气道关键设计参数的影响
Table 5. Effect of transverse spacing of the jet slot ΔY on inlet key design parameters
关键设计参数 数值 射流缝横向间距ΔY 0.160D
0.184D
0.207D
0.229D
0.252D射流缝1横向位置Y 0.223D 射流角θ/（°） 36 进气道长度 4D 面积扩张比γad 1.3
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表 6 射流缝不同横向间距ΔY进气道气动性能参数
Table 6. Aerodynamic performance parameters of different transverse spacing of the jet slot ΔY
ΔY Ma2 σ δ60 0.160D 0.5037 0.8897 0.5942 0.184D 0.5008 0.8892 0.4793 0.207D 0.4984 0.8885 0.4592 0.229D 0.4970 0.8877 0.5046 0.252D 0.4967 0.8872 0.5271
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表 7 射流缝1横向位置Y对进气道关键设计参数的影响
Table 7. Effect of ransverse position of the jet slot one Y on inlet key design parameters
关键设计参数 数值 射流缝横向间距ΔY 0.207D
0.094D
0.161D射流缝1横向位置Y 0.223D
0.289D
0.350D射流角θ/（°） 36 进气道长度 4D 面积扩张比γad 1.3
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表 8 不同射流缝1横向位置Y进气道气动性能参数
Table 8. Aerodynamic performance parameters of different transverse position of the jet slot one Y
Y Ma2 σ δ60 0.094D 0.504 0.8893 0.5378 0.161D 0.4982 0.8886 0.3915 0.223D 0.4984 0.8885 0.4592 0.289D 0.4953 0.8869 0.3608 0.350D 0.4952 0.8866 0.4191
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表 9 射流角度θ对进气道关键设计参数的影响
Table 9. Effect of jet angle θ on inlet key design parameters
关键设计参数 数值 射流缝横向间距ΔY 0.207D 射流缝1横向位置Y 0.289D 射流角θ/（°） 33
36
39
42
48
51
54进气道长度 4D 面积扩张比γad 1.3
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表 10 不同射流角θ进气道气动性能参数
Table 10. Inlet aerodynamic performance parameters of different jet angle θ
θ/（°） Ma2 σ δ60 33 0.4970 0.8876 0.4247 36 0.4953 0.8869 0.3608 39 0.4952 0.8866 0.3885 42 0.4943 0.8860 0.3866 48 0.4933 0.8856 0.3277 51 0.4934 0.8857 0.2880 54 0.4936 0.8862 0.3413
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表 11 射流面积比γab对进气道关键设计参数的影响
Table 11. Effect of jet area ratio γab on inlet key design parameters
关键设计参数 数值 射流缝横向间距ΔY 0.207D 射流缝1横向位置Y 0.289D 射流角θ/（°） 51 射流面积比γab/% 0.6867 0.7848 0.8829 0.9319 0.9810 1.0300 进气道长度 4D 面积扩张比γad 1.3
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表 12 不同射流面积比γab进气道气动性能参数
Table 12. Inlet aerodynamic performance parameters of different jet area ratios γab
γab/% Ma2 σ δ60 0.6867 0.4964 0.8870 0.5072 0.7848 0.4952 0.8863 0.4296 0.8829 0.4943 0.8860 0.3614 0.9319 0.4938 0.8858 0.3266 0.9810 0.4934 0.8857 0.2880 1.0300 0.4930 0.8857 0.3048
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