| タイトル | Results of low power deicer tests on a swept inlet component in the NASA Lewis icing research tunnel |
| 本文（外部サイト） | http://hdl.handle.net/2060/19930005722 |
| 著者（英） | Bond, Thomas H.; Shin, Jaiwon |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1993-01-01 |
| 言語 | eng |
| 内容記述 | Tests were conducted under a USAF/NASA Low Power Deicer program on two expulsive technologies to examine system performance on hardware representative of a modern aircraft part. The BF Goodrich Electro-Expulsive Deicing System and Pneumatic Impulse Ice Protection System were installed on a swept, compound curve, engine inlet component with varying leading edge radius, and tested through a range of icing and system operating conditions in the NASA Lewis Icing Research Tunnel. A description of the experimental procedure and results, including residual ice thickness, shed ice particle size, and changes in system energy/pressure characteristics are presented. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 93N14911
NASA-TM-105968
E-7495
NAS 1.15:105968
AIAA PAPER 93-0032 |
| 権利 | No Copyright |
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