2018年
Effect of Mach number on airfoil characteristics at Reynolds number of 3,000
Transactions of the Japan Society for Aeronautical and Space Sciences
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- 巻
- 61
- 号
- 6
- 開始ページ
- 258
- 終了ページ
- 267
- 記述言語
- 英語
- 掲載種別
- 研究論文(学術雑誌)
- DOI
- 10.2322/tjsass.61.258
© 2018 The Japan Society for Aeronautical and Space Sciences. The effects of Mach number at Re = 3,000 for different airfoils (NACA0012, NACA0002, NACA4412, NACA4402) with thickness and camber geometries are investigated for the propeller blade design of a Mars airplane. The present study shows that thin and cambered airfoils have larger variations in Cl than symmetric airfoils. As for thin airfoils, Cl at higher ¡ has rapid increases when the M¨ is low. This is because the flow separation occurs at the leading edge, and the flow is reattached on the airfoil surface. However, the rapid increase in Cl disappear as M¨ increases because the flow reattachment does not occurs. As for cambered airfoils, the decrease in Cl becomes larger than that on the symmetric airfoils when M¨ is higher. This is because Cp near the leading edge on the lower surface is smaller than that on the upper surface and the high-speed region on the lower side of the leading edge is enlarged as M¨ increases. Then, the Mcr at Re = 3,000 tends to be larger than that predicted by linear theory.
- リンク情報
- ID情報
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- DOI : 10.2322/tjsass.61.258
- ISSN : 0549-3811
- SCOPUS ID : 85056140831