Title: Influence of trailing edge tab on moment characteristics of NACA 23012 airfoil
Abstract: Abstract A comparison of predicted and measured aerodynamic characteristics of the original NACA 23012 airfoil and an airfoil with a trailing edge tab is presented. XFOIL code is used for prediction. It is shown that the modification of the airfoils only on the upper side at the trailing edge affects practically only moment characteristics. An example of the airfoil modification with zero moment coefficients is presented.
Publication Year: 2007
Publication Date: 2007-12-31
Language: en
Type: article
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Cited By Count: 1
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