衝撃風洞における感圧塗料計測法について

DOI Web Site Web Site 被引用文献4件 参考文献14件
  • 栗田 充
    名古屋大学大学院工学研究科航空宇宙工学専攻
  • 岡田 拓己
    名古屋大学大学院工学研究科航空宇宙工学専攻
  • 中村 佳朗
    名古屋大学大学院工学研究科航空宇宙工学専攻

書誌事項

タイトル別名
  • Pressure-Sensitive Paint Measurements of Hypersonic Flow in Shock Tunnel
  • 衝撃風洞における感圧塗料計算法について
  • ショウゲキ フウドウ ニ オケル カンアツ トリョウ ケイサンホウ ニ ツイテ

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抄録

The use of pressure sensitive paint can make possible the measurement of global surface pressure distribution on a body at a time, which is different from point measurement by conventional pressure transducers. Although shock tunnels have been widely used to make hypersonic flows at low cost and to examine the flowfield around re-entry vehicles, they have a limitation of duration. The present paper proposes a new pressure sensitive paint method for hypersonic flows in shock tunnel. To realize its fast response, we developed a paint method, the results of which were compared with detailed pressure measurements by using conventional pressure transducers as well as visualizations by Schlieren photography and oil flow method. As a result, the present method was found to be useful and effective to analyze the flowfield around body in shock tunnel.

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