| タイトル | Investigation of two bifurcated-duct inlet systems from Mach 0 to 2.0 over a wide range of angles of attack |
| 本文（外部サイト） | http://hdl.handle.net/2060/19760020078 |
| 著者（英） | Latham, E. A. |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 1976-05-01 |
| 言語 | eng |
| 内容記述 | A 15.354 percent/scale lightweight fighter type inlet/forebody was tested over a Mach number range of 0 to 2.0. Model configurations consisted of side mounted normal shock and fixed overhead ramp type inlets. Each configuration consisted of two inlets ducted (bifurcated) to supply a single engine face. The normal shock inlet variables included a boundary layer splitter bleed system, alternate boundary layer splitter plates, alternate upper and lower cowl lip shapes, and a blow-in-door (auxiliary inlet) in one lower lip. The only variable of the fixed overhead ramp inlet was the boundary layer bleed flow. Reynolds numbers ranged from 7.6 x 1 million to 19.5 x 1 million/m. Angle of attack ranged from -10 to 35 deg and angle of sideslip from -8 to 8 deg. Test measurements included engine face total pressure recovery, steady state distortion, dynamic distortion, and surface static pressures on the forebody and inlet surfaces. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 76N27166
NASA-TM-X-73118
A-6512 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/185359 |
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