Influence of trailing edge tab on moment characteristics of NACA 23012 airfoil
DOI: https://doi.org/10.3846/16487788.2007.9635970Abstract
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.
First published online: 14 Oct 2010
Keywords:
airfoil, trailing edge tab, moment characteristicsHow to Cite
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Copyright (c) 2007 The Author(s). Published by Vilnius Gediminas Technical University.
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Copyright (c) 2007 The Author(s). Published by Vilnius Gediminas Technical University.
License
This work is licensed under a Creative Commons Attribution 4.0 International License.