| タイトル | Acoustic and Aero-Mixing Experimental Results for Fluid Shield Scale Model Nozzles |
| 本文（外部サイト） | http://hdl.handle.net/2060/20050080678 |
| 著者（英） | Salikuddin, M.; Majjigi, R. K.; Mengle, V. G.; Shin, H. W. |
| 著者所属（英） | General Electric Aircraft Engines |
| 発行日 | 2005-02-01 |
| 言語 | eng |
| 内容記述 | The principle objectives of this investigation are to evaluate the acoustic and aerodynamic characteristics of fluid shield nozzle concept and to assess Far 36, Stage 3 potential for fluid shield nozzle with Flade Cycle. Acoustic data for nine scale model nozzle configurations are obtained. The effects of simulated flight and geometric and aerothermodynamic flow variables on the acoustic behavior of the fluid shield are determined. The acoustic tests are aimed at studying the effect of: (1) shield thickness, (2) wrap angle, (3) mass flow and velocity ratios between shield and core streams at constant cycle specific thrust (i.e., mixed velocity), (4) porous plug, and (5) subsonic shield. Shadowgraphs of six nozzle configurations are obtained to understand the plume flowfield features. Static pressure data on suppressor chutes in the core stream (shielded and unshielded) sides and on plug surface are acquired to determine the impact of fluid shield on base drag of the 36-chute suppressor nozzle and the thrust augmentation due to the plug, respectively. |
| NASA分類 | Acoustics |
| レポートNO | NASA/CR-2005-213213
E-14721 |
| 権利 | No Copyright |
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