Share:


Influence of trailing edge tab on moment characteristics of NACA 23012 airfoil

    Eduardas Lasauskas Affiliation
    ; Thorsten Lutz Affiliation
    ; Markus Dietz Affiliation

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.


First published online: 14 Oct 2010

Keyword : airfoil, trailing edge tab, moment characteristics

How to Cite
[1]
Lasauskas, E., Lutz, T. and Dietz, M. 2007. Influence of trailing edge tab on moment characteristics of NACA 23012 airfoil. Aviation. 11, 4 (Dec. 2007), 3-8. DOI:https://doi.org/10.3846/16487788.2007.9635970.
Published in Issue
Dec 31, 2007
Abstract Views
51
PDF Downloads
33