Influence of DSI two-stage swept back lip on aircraft external flow
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摘要:
为研究无隔道超声速进气道（DSI）唇口对飞机整体气动性能的影响，采用数值仿真方法对全机进行了三维内外流场的数值模拟。以进气道性能最优的单级后掠唇口为基准模型，在此基础上设计了两级斜切后掠唇口模型。研究发现与基准唇口相比，两级斜切后掠唇口模型不仅能够提高进气道的总压恢复系数，改善进气道的出口流场畸变；而且能够通过改变机翼表面的压力分布来改变机翼的升力，进而影响飞机整体的气动力特性。结果表明：在本文所研究的两级斜切后掠唇口不同的二级后掠角变化范围内，存在最佳后掠角度35°可以进一步提高全机气动布局升阻比，升阻比提高了0.034，其增益可达2.1%。
Abstract:In order to study the influence of diverterless supersonic inlet (DSI) lip on the overall aerodynamic performance of the aircraft, the internal and external flow fields were simulated by numerical simulation method. Based on the benchmark model of single-stage swept back lip with the optimal inlet performance, a two-stage swept back lip model was designed. It was found that compared with benchmark model, the two-stage swept back lip model can not only improve the total pressure recovery coefficient and reduce the flow distortion index of the inlet, but also change the lift of the wing by changing the pressure distribution on the wing surface, and then affect the aerodynamic characteristics of the aircraft as a whole. Within the range of two-stage sweep back angle in this study, an optimal angle 35° can help further improve the lift-drag ratio of the aircraft aerodynamic layout by 0.034, and the gain up to 2.1%.
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图 10 DSI两级斜切后掠唇口性能曲线图
Figure 10. Performance comparison of two-stage swept back lip of DSI
图 14 不同两级斜切后掠唇口空间流场参数分布
Figure 14. Parameters distribution of flow field with different two-stage swept back lips
图 15 不同两级斜切后掠唇口机翼上下表面压力分布
Figure 15. Surface pressure contour of wing with different two-stage swept back lips
图 16 不同唇口构型机翼不同站位剖面压力系数分布
Figure 16. Pressure coefficient distribution of station profiles with different lip models
图 17 两级斜切后掠唇口飞机沿流向静压分布切面图
Figure 17. Static pressure distribution along flow direction of aircraft with two-stage swept back lip
图 18 不同唇口的飞机升阻比随飞行攻角的变化
Figure 18. Lift-drag ratio of aircraft with different lips at different flight angles of attack
表 1 不同网格量计算结果
Table 1. Calculation results of different grids
网格数量/104 升力系数CL 阻力系数CD 500 0.0361 0.0228 800 0.0368 0.0229 1100 0.0369 0.0228 1250 0.0369 0.0228 
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表 2 试验来流条件
Table 2. Incoming flow conditions of test
参数 数值 Ma∞ 1.4 P*/105 Pa 2.3 P/Pa 72275.4 T/K 270.2
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表 3 DSI单级后掠唇口性能参数
Table 3. Performance parameters of single-stage swept back lip of DSI
α/（°） σ Cd60 Pb/Pa 0 0.9339 1.0773 54381.4 15 0.9626 0.3976 56387.5 30 0.9706 0.1484 56876.6 40 0.9704 0.1539 56890.8
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表 4 两级斜切后掠唇口飞机气动性能
Table 4. Aerodynamic performance of two-stage swept back lip（aircraft）
β/（°） CL-total CD-total CL/CD 30 0.0369 0.0228 1.6198 32.5 0.0371 0.0226 1.6380 35 0.0373 0.0226 1.6542 37.5 0.0372 0.0226 1.6499 40 0.0361 0.0226 1.5967 45 0.0346 0.0227 1.5214
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表 5 两级斜切后掠唇口机翼气动性能
Table 5. Aerodynamic performance of two-stage swept back lip （wing）
β/（°） CL-wing CD-wing 30 0.0430 0.0071 32.5 0.0432 0.0071 35 0.0434 0.0070 37.5 0.0434 0.0070 40 0.0426 0.0069 45 0.0414 0.0071
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