University of Tokyo Graduate School
Japan Aerospace Exploration Agency Institute of Space and Astronautical Science
Japan Aerospace Exploration Agency Institute of Space and Astronautical Science
出版者
宇宙航空研究開発機構宇宙科学研究本部
出版者（英）
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)
雑誌名
宇宙航行の力学シンポジウム 平成15年度
雑誌名(英)
Symposium on Flight Mechanics and Astrodynamics 2003
ページ
39 - 42
発行年
2004-05
抄録（英）
Understanding on an efficient small-scale hovering rotor is required to make a miniature rotorcraft probe to explore the Martian surface. For this purpose, an experimental measurement of the aerodynamic characteristics of a small-scale rotor at ultra-low Reynolds numbers (Re = 2,000, 4,000, 8,000) was performed. The experimental results show that the airflow around the rotor is subject to the leading-edge vortex (LEV) and that the Blade Element Momentum Theory (BEMT) is valid at moderate collective pitch angles and that the capability of the rotor required for the rotorcraft probe is within reach.
火星探査機用回転翼の超低レイノルズ数空力特性
