| タイトル | Advanced Nacelle Acoustic Lining Concepts Development |
| 本文（外部サイト） | http://hdl.handle.net/2060/20020079889 |
| 著者（英） | Bielak, G.; Yu, J.; Premo, J.; Celano, J.; Kunze, R.; Hersh, A.; Parrott, Tony L.; Murray, P.; Walker, B.; Kosanchick, M.; Gallman, J. |
| 著者所属（英） | Boeing Commercial Airplane Co. |
| 発行日 | 2002-08-01 |
| 言語 | eng |
| 内容記述 | The work reported in this document consisted of six distinct liner technology development subtasks: 1) Analysis of Model Scale ADP Fan Duct Lining Data (Boeing): An evaluation of an AST Milestone experiment to demonstrate 1995 liner technology superiority relative to that of 1992 was performed on 1:5.9 scale model fan rig (Advanced Ducted Propeller) test data acquired in the NASA Glenn 9 x 15 foot wind tunnel. The goal of 50% improvement was deemed satisfied. 2) Bias Flow Liner Investigation (Boeing, VCES): The ability to control liner impedance by low velocity bias flow through liner was demonstrated. An impedance prediction model to include bias flow was developed. 3) Grazing Flow Impedance Testing (Boeing): Grazing flow impedance tests were conducted for comparison with results achieved at four different laboratories. 4) Micro-Perforate Acoustic Liner Technology (BFG, HAE, NG): Proof of concept testing of a "linear liner." 5) Extended Reaction Liners (Boeing, NG): Bandwidth improvements for non-locally reacting liner were investigated with porous honeycomb core test liners. 6) Development of a Hybrid Active/Passive Lining Concept (HAE): Synergism between active and passive attenuation of noise radiated by a model inlet was demonstrated. |
| NASA分類 | Acoustics |
| レポートNO | NASA/CR-2002-211672
NAS 1.26:211672 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/91184 |
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