Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
JAXA Special Publication: FY2004 Report of Joint Research Achievements of the Space Division of Institute of Aerospace Technology and Institute of Space and Astronautical Science: Basic Technologies of Space Transportation Systems
巻
JAXA-SP-05-010
ページ
63 - 68
発行年
2006-01-20
抄録（英）
A designing concept for the inlet of the combined cycle engine was explored in the current study. The models designed by the concept were tested in several wind tunnels, ranging from subsonic to hypersonic air speed. The experimental results showed the decrease of the pressure drag in sub/transonic regime. In supersonic condition, the new model proved the high starting capability. However, in hypersonic range, the inlets lost more mass flow than expected, due to the skewed shock structure. Further studies will be required to establish optimized geometry of the inlet.
静止から極超音速域までの複合エンジンインレット性能改善試験について
49056014.pdf
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