| タイトル | Blended Wing Body Systems Studies: Boundary Layer Ingestion Inlets With Active Flow Control |
| 本文（外部サイト） | http://hdl.handle.net/2060/20040031343 |
| 著者（英） | Geiselhart, Karl A.; Daggett, David L.; Kawai, Ron; Friedman, Doug |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2003-12-01 |
| 言語 | eng |
| 内容記述 | A CFD analysis was performed on a Blended Wing Body (BWB) aircraft with advanced, turbofan engines analyzing various inlet configurations atop the aft end of the aircraft. The results are presented showing that the optimal design for best aircraft fuel efficiency would be a configuration with a partially buried engine, short offset diffuser using active flow control, and a D-shaped inlet duct that partially ingests the boundary layer air in flight. The CFD models showed that if active flow control technology can be satisfactorily developed, it might be able to control the inlet flow distortion to the engine fan face and reduce the powerplant performance losses to an acceptable level. The weight and surface area drag benefits of a partially submerged engine shows that it might offset the penalties of ingesting the low energy boundary layer air. The combined airplane performance of such a design might deliver approximately 5.5% better aircraft fuel efficiency over a conventionally designed, pod-mounted engine. |
| NASA分類 | Aircraft Design, Testing and Performance |
| レポートNO | NASA/CR-2003-212670 |
| 権利 | No Copyright |
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