Open AccessINFLUENCE OF TRAILING EDGE TAB ON MOMENT CHARACTERISTICS OF NACA 23012 AIRFOIL
Author(s) -
Eduardas Lasauskas,
Thorsten Lutz,
Markus Dietz
Publication year - 2007
Publication title -
aviation
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.239
H-Index - 13
eISSN - 1822-4180
pISSN - 1648-7788
DOI - 10.3846/16487788.2007.9635970
Subject(s) - airfoil , trailing edge , naca airfoil , pitching moment , aerodynamics , moment (physics) , leading edge , angle of attack , mechanics , structural engineering , physics , engineering , reynolds number , classical mechanics , turbulence
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.