摘要
In order to quantificationally investigate the aerodynamics of flapping-wing MAV (Micro Air Vehicle), the wind tunnel test of flapping-wing MAV is performed in special micro air vehicle wind tunnel of NPU (Northwestern Polytechnical University). The effects of flapping frequency, wind velocity, angle of attack, plane shape of wing and cambered aerofoil are investigated. In this experiment the producing rules of lift and thrust are found. The result of experiment can guide the conceptual design and aerodynamic design of the flapping-wing MAV.
| 源语言 | 英语 |
|---|---|
| 页（从-至） | 275-280 |
| 页数 | 6 |
| 期刊 | Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica |
| 卷 | 28 |
| 期 | 2 |
| 出版状态 | 已出版 - 3月 2007 |