Experimental Study on the Wing Lift Characteristics of Biplane Micro Air Vehicle

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  • AKIYAMA Kohei
    東京大学大学院
  • TEZUKA Asei
    東京大学大学院工学系研究科航空宇宙工学専攻 現 早稲田大学理工学術院基幹理工学部機械科学・航空学科
  • SUNADA Yasuto
    東京大学大学院工学系研究科航空宇宙工学専攻
  • RINOIE Kenichi
    東京大学大学院工学系研究科航空宇宙工学専攻

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Other Title
  • 複葉型超小型航空機の主翼揚力特性に関する実験
  • フクヨウガタ チョウコガタ コウクウキ ノ シュヨク ヨウリョク トクセイ ニ カンスル ジッケン

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This paper investigates wing aerodynamic characteristics used for bi-plane micro-air vehicles. Surface pressure distributions of two-dimensional biplane airfoils (4% cambered-plate airfoil) were measured at a chord Reynolds number of 6.4 × 104. Lift characteristics of three-dimensional biplane rectangular wings (aspect ratio of 3) were also measured at the same Reynolds number. It was indicated that the behaviors of laminar separation bubble formed both on the upper and lower airfoils/wings affects their lift characteristics. Bi-plane wings with positive stagger, i.e. protruded upper wing indicated higher maximum lift coefficient. This is caused by different behaviors of laminar separation bubble formed on the wing.

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