Development of low density wind tunnel to simulate atmospheric flight on Mars

M. Anyoji, H. Nagai, K. Asai

研究成果: 書籍/レポート タイプへの寄稿会議への寄与

13 被引用数 (Scopus)

抄録

A new type of wind tunnel that can simulate airfoil flow in the Mars atmosphere has been designed and constructed at Tohoku University. This wind tunnel is driven by ejector and designed to simulate low-density Martian atmosphere consisting of CO2. The preliminary performance tests were conducted using air to investigate the operating envelop of the tunnel. It was demonstrated that this wind tunnel could cover the Reynolds number range from 104 to 105 and the Mach number range up to 0.71, allowing us to simulate low Reynolds number and high subsonic flow on Mars airplanes. Calibration tests were also conducted to investigate the flow characteristics in the test section. It was confirmed that the flow was kept uniform in the test section even when the total pressure was 1 kPa. There were significant effects of the boundary layer development on static pressure gradient along the test section. It was found that these effects of boundary layers could be corrected by inclining both the upper and lower walls of the test section.

本文言語英語
ホスト出版物のタイトル47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition
出版社American Institute of Aeronautics and Astronautics Inc.
ISBN(印刷版)9781563479694
DOI
出版ステータス出版済み - 2009
外部発表はい

出版物シリーズ

名前47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition

!!!All Science Journal Classification (ASJC) codes

  • 宇宙惑星科学
  • 航空宇宙工学

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