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- W2330233523 abstract "A supersonic air-inlet with bypass technique intended to reduce spillage drag was designed based on a characteristic of an actual jet engine. The effects of bypass design on drag reduction and pressure recovery was examined using CFD simulation. It was found that the bypass design gives a significant drag reduction as well as improves pressure recovery of inlet. The decrement of inlet drag largely surpasses the increment of the nacelle drag within the engine operating range. Furthermore, the bypass duct should be closed when an inlet operates in supercritical condition. Additionally, aerodynamic performance of inlet with diverterless configuration was evaluated to investigate the effects of boundary layer ingestion from airframe surface. In order to improve the inlet performance, a half-conical ramp was adopted to external compression inlet design. It became clear that, thick boundary-layer ingestion causes a huge flow separation within a conventional type inlet, and both pressure recovery and spatial distortion decay drastically. The half-conical ramp prevents boundary-layer from separating, and it is a promising option for diverterless inlet design." @default.
- W2330233523 created "2016-06-24" @default.
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- W2330233523 date "2014-07-25" @default.
- W2330233523 modified "2023-09-22" @default.
- W2330233523 title "Low Drag Design and Aerodynamic Performance Evaluation of Supersonic Air Inlet" @default.
- W2330233523 cites W2030121990 @default.
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- W2330233523 doi "https://doi.org/10.2514/6.2014-3798" @default.
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