Flow field structure of stealth inlet under ground state
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摘要:
为探明隐身进气道在地面状态下流场恶劣的原因，分别对三角形和M形等斜切口面进气道在地面状态下的流场结构进行数值仿真分析，并研究了唇口占比和内通道偏距对M形进口进气道地面工作特性的影响规律。结果表明：三角形口面进气道在进口对称面附近形成一个巨大的三维分离涡（一半流场），而M形口面进气道在侧唇口和上唇口交汇处形成一对尺度相对较小的旋涡，而且三角形口面进气道出口畸变指数过大，难以满足进/发匹配要求。随着M形口面唇口占比的增加，进气道出口截面低总压区沿着侧壁逆时针偏转，并且涡旋方向发生改变，总压恢复系数逐渐增大，畸变指数先减小后增加。内通道偏距的增大会进一步加剧地面状态下流场的恶化。
Abstract:In order to find out the cause of bad flow field of the stealthy inlet under the ground state, the flow field structure of the triangular and M-shaped inlets with equal inclined cut surface under the ground state was numerically simulated and analyzed, and the influences of the lip ratio and internal channel offset on the ground working characteristics of the M-shaped inlet were studied. The results showed that a large three-dimensional separated vortex (half flow field) was formed near the inlet symmetry plane in the triangular inlet, while a pair of relatively small vortices were formed at the intersection of the side lip and the upper lip in the M-shaped inlet. Moreover, the distortion index at the outlet of the triangular inlet was too large to meet the inlet/engine matching requirements. With the increase of the proportion of the M-shaped lip, the low total pressure area of the inlet exit section deflected counterclockwise along the sidewall, and the direction of the vortex changed. The total pressure recovery coefficient gradually increased, and the distortion index decreased first and then increased. The increase of internal channel offset could further aggravate the deterioration of flow field under ground conditions.
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图 1 隐身无人机半模示意图
Figure 1. Schematic diagram of semi model of stealth unmanned aerial vehicle （UAV）
图 3 网格数为4.4×106时计算得到的进气道出口总压恢复系数分布与实验结果对比
Figure 3. Comparison between the distribution of total pressure recovery coefficient at the inlet outlet calculated with a grid size of 4.4×106 and experimental results
图 7 三角形进口进气道总压恢复系数分布云图
Figure 7. Cloud chart of total pressure recovery coefficient distribution of triangular inlet
图 8 三角形进口进气道对称面马赫数云图
Figure 8. Mach number nephogram of symmetric plane of triangular inlet
图 10 M形进口进气道总压恢复系数分布云图
Figure 10. Cloud chart of total pressure recovery coefficient distribution of M-shaped inlet
图 11 M形进口进气道对称面马赫数云图
Figure 11. Mach number cloud diagram of symmetric plane of M-shaped inlet
图 13 不同唇口占比进气道地面状态下气动性能曲线图
Figure 13. Curve of aerodynamic performance parameters of inlet under ground conditions with different lip ratios
图 14 不同唇口占比进气道方案口面流线图
Figure 14. Flow line diagram of inlet port with different lip ratios
图 15 不同唇口占比进气道方案沿程及出口截面总压恢复系数分布云图
Figure 15. Cloud chart of total pressure recovery coefficient distribution along the path and exit section of inlet with different lip proportions
图 16 不同唇口占比进气道巡航状态下气动性能参数曲线图
Figure 16. Aerodynamic performance parameter curve of inlet under cruise condition with different lip ratios
图 17 不同内通道偏距进气道方案在地面状态下气动性能参数曲线图
Figure 17. Aerodynamic performance parameters curve of different internal channel offset inlet schemes under ground conditions
图 18 不同偏距进气道方案沿程截面总压恢复系数分布云图
Figure 18. Cloud chart of total pressure recovery coefficient distribution along the cross section of different offset inlet schemes
图 19 不同偏距进气道方案对称面马赫数分布云图
Figure 19. Cloud chart of mach number distribution on symmetric plane of different offset inlet schemes
图 20 不同偏距进气道方案出口截面总压恢复系数和二次流分布云图
Figure 20. Cloud chart of total pressure recovery coefficient and secondary flow distribution at outlet section of different offset inlet schemes
表 1 仿真与实验性能参数对比
Table 1. Comparison of simulation and experimental performance parameters
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 IDC（60） 0.2983 0.3204 0.2747 0.2774 0.2992 
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表 2 三角形和M形口面进气道地面状态下气动性能参数对比
Table 2. Comparison of aerodynamic performance parameters of triangular and M-shaped inlet under ground conditions
性能参数 口面形式 三角形 M形 Ma2 0.5022 0.5050 σ 0.8894 0.8944 IDC（60） 0.8164 0.2727
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