| タイトル | Development of Micro Air Vehicle Technology With In-Flight Adaptive-Wing Structure |
| 本文（外部サイト） | http://hdl.handle.net/2060/20040161133 |
| 著者（英） | Wagner, Matthew; Waszak, Martin R.; Shkarayev, Sergey; Null, William |
| 著者所属（英） | Arizona Univ.; NASA Langley Research Center |
| 発行日 | 2004-10-01 |
| 言語 | eng |
| 内容記述 | This is a final report on the research studies, "Development of Micro Air Vehicle Technology with In-Flight Adaptrive-Wing Structure". This project involved the development of variable-camber technology to achieve efficient design of micro air vehicles. Specifically, it focused on the following topics: 1) Low Reynolds number wind tunnel testing of cambered-plate wings. 2) Theoretical performance analysis of micro air vehicles. 3) Design of a variable-camber MAV actuated by micro servos. 4) Test flights of a variable-camber MAV. |
| NASA分類 | Aircraft Design, Testing and Performance |
| レポートNO | NASA/CR-2004-213271 |
| 権利 | No Copyright |
