| タイトル | Low speed test of the aft inlet designed for a tandem fan V/STOL nacelle |
| 本文（外部サイト） | http://hdl.handle.net/2060/19800009778 |
| 著者（英） | Ybarra, A. H.; Rhoades, W. W. |
| 著者所属（英） | Vought Corp. |
| 発行日 | 1980-02-01 |
| 言語 | eng |
| 内容記述 | An approximately .25 scale model of a Tandem Fan nacelle designed for a Type A V/STOL aircraft configuration was tested in a 10-by-10 foot wind tunnel. A 12 inch, tip driven, turbofan simulator was used to provide the suction source for the aft fan inlet. The front fan inlet was faired over for this test entry. Model variables consisted of a long aft inlet cowl, a short aft inlet cowl, a shaft simulator, blow-in door passages and diffuser vortex generators. Inlet pressure recovery, distortion, inlet angle of attack separation limits were evaluated at tunnel velocities from 0 to 240 knots, angles of attack from -10 to 40 degrees and inlet flow rates representative of throat Mach numbers of 0.1 to 0.6. High inlet performance and stable operation was verified at all design forward speed and angle of attack conditions. The short aft inlet configuration provided exceptionally high pressure recovery except at the highest combination of angle of attack and forward speed. The flow quality at the fan face was somewhat degraded by the addition of blow-in door passages to the long aft inlet configuration due to the pressure disturbances generated by the flow entering the diffuser through the auxiliary air passages. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 80N18042
NASA-CR-159752
TR-2-30320/OR-52360 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/173311 |
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