Description of an experimental investigation concerning the nonlinear lift characteristics of a thick symmetric airfoil at zero incidence where the lift curve slope turns to be negative. Detailed studies on the flow around the airfoil and the surface pressure distribution show that the nonlinear behavior is related to the flow separation near the trailing edge. While in laminar flow no separation is found, a large separated region is observed near the end of the airfoil in turbulent flow. The pressure distribution in turbulent flow also differes much from the one in laminar flow. The separation near the body end makes the pressure difference between both sides of the airfoil not restricted in the tail region, but spread over the entire chord length.
Nonlinear lift characteristics of thick symmetric airfoil at zero incidence
Nichtlineare Auftriebseigenschaften des dicken symmetrischen Tragfluegels bei einem Anstellwinkel von Null
Journal of the Kansai Society of Naval Architects ; 56 , 181 ; 55-62
1981
8 Seiten, 15 Bilder, 3 Tabellen, 11 Quellen
Article (Journal)
English
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