| タイトル | Energy Efficient Engine Program Advanced Turbofan Nacelle Definition Study |
| 本文（外部サイト） | http://hdl.handle.net/2060/19900019244 |
| 著者（英） | Howe, David C.; Wynosky, T. A. |
| 著者所属（英） | Pratt and Whitney Aircraft |
| 発行日 | 1985-05-01 |
| 言語 | eng |
| 内容記述 | Advanced, low drag, nacelle configurations were defined for some of the more promising propulsion systems identified in the earlier Benefit/Cost Study, to assess the benefits associated with these advanced technology nacelles and formulate programs for developing these nacelles and low volume thrust reversers/spoilers to a state of technology readiness in the early 1990's. The study results established the design feasibility of advanced technology, slim line nacelles applicable to advanced technology, high bypass ratio turbofan engines. Design feasibility was also established for two low volume thrust reverse/spoiler concepts that meet or exceed the required effectiveness for these engines. These nacelle and thrust reverse/spoiler designs were shown to be applicable in engines with takeoff thrust sizes ranging from 24,000 to 60,000 pounds. The reduced weight, drag, and cost of the advanced technology nacelle installations relative to current technology nacelles offer a mission fuel burn savings ranging from 3.0 to 4.5 percent and direct operating cost plus interest improvements from 1.6 to 2.2 percent. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 90N28560
NASA-CR-174942
NAS 1.26:174942
PWA-5394-315 |
| 権利 | Copyright, Public use permitted |
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