Effect of Mach number on airfoil characteristics at Reynolds number of 3,000

Seiichiro Morizawa, Taku Nonomura, Akira Oyama, Kozo Fujii, Shigeru Obayashi

Research output: Contribution to journalArticlepeer-review

6 Citations (Scopus)


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.

Original languageEnglish
Pages (from-to)258-267
Number of pages10
JournalTransactions of the Japan Society for Aeronautical and Space Sciences
Issue number6
Publication statusPublished - 2018 Jan 1


  • Airfoil Characteristics
  • Low-Reynolds Number
  • Mach-number Effect
  • Mars Airplane

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science


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