| タイトル | Wind tunnel investigation of simulated helicopter engine exhaust interacting with windstream |
| 本文（外部サイト） | http://hdl.handle.net/2060/19740009645 |
| 著者（英） | Wilson, J. C.; Shaw, C. S. |
| 著者所属（英） | NASA Langley Research Center|Army Air Mobility Research and Development Lab. |
| 発行日 | 1974-03-01 |
| 言語 | eng |
| 内容記述 | A wind tunnel investigation of the windstream-engine exhaust flow interaction on a light observation helicopter model has been conducted in the Langley V/STOL tunnel. The investigation utilized flow visualization techniques to determine the cause to determine the cause of exhaust shield overheating during cruise and to find a means of eliminating the problem. Exhaust flow attachment to the exhaust shield during cruise was found to cause the overheating. Several flow-altering devices were evaluated to find a suitable way to correct the problem. A flow deflector located on the model cowling upstream of the exhaust in addition to aerodynamic shield fairings provided the best solution. Also evaluated was heat transfer concept employing pin fins to cool future exhaust hardware. The primary flow visualization technique used in the investigation was a newly developed system employing neutrally buoyant helium-filled bubbles. The resultant flow patterns were recorded on motion picture film and on television magnetic tape. |
| NASA分類 | AIRCRAFT |
| レポートNO | 74N17758
NASA-TM-X-3016
L-9430 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/195690 |
