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Coupled numerical simulation of the external and engine inlet flows for the F-18 at large incidence

机译：F-18大进气量时外部和发动机进气流的耦合数值模拟

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This paper presents a numerical simulation of the external and engine inlet flows for the F-18 aircraft at typical high-angle-of attack flight conditions. Two engine inlet mass flow rates, corresponding to flight idle and maximum power, were computed. This was accomplished using a structured, overset grid technique to couple the external and internal grid systems. Reynolds-averaged Navier--Stokes solutions were obtained using an implicit, finite-differencing scheme. Results show a strong coupling of the external and engine inlet flows, especially at the maximum power setting. Increasing the mass flow rate through the inlet caused the primary vortex breakdown location to move downstream. This trend is also observed in flight tests performed on the F-18. A reversed flow region upstream of the inlet duct is visible in the faired-inlet and flight-idle computations. This flow reversal is not present in the maximum power setting computation. These large-scale changes in flow structure highlight the importance of simulating inlet conditions in high-angle- of attack aircraft computations.
机译：本文介绍了F-18飞机在典型的高攻角飞行条件下外部和发动机进气流的数值模拟。计算了两个发动机进气口质量流率，分别对应于空转和最大功率。这是通过使用结构化的覆盖网格技术将外部和内部网格系统耦合来完成的。使用隐式有限差分方案获得雷诺平均Navier-Stokes解。结果表明，尤其是在最大功率设置下，外部和发动机进气流之间的耦合很强。通过入口的质量流率增加导致初级涡旋破裂位置向下游移动。在F-18上进行的飞行测试中也观察到了这种趋势。在整流罩入口和空转怠速计算中可以看到入口管道上游的反向流动区域。最大功率设置计算中不存在这种逆流。流动结构的这些大规模变化突显了在高攻角飞机计算中模拟进气口条件的重要性。

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