An analysis of pressure difference on airfoil by changing angle of attack and gurney flap height

Volume : IV, Issue : IV, April - 2015

Hardik S. Patel

The present study comprises steady state, two–dimensional computational investigations performed on NACA0012

(National advisory committee for aeronautics) airfoil to analyse the effect of pressure difference on airfoil with GF (gurney

flap) at various angle of attack using viscous–laminar model of FLUENT & using CAD preparation of two dimensional

NACA 0012 airfoil. Airfoil with GF is analysed for four different heights from 0%to 6% of the chord length and three angles of attack from 0? to

16?. Static pressure distribution on the airfoil surface is present. From computational investigation, it is recommended that Gurney flaps with a

approximately height of 4% chord to be installed perpendicular to chord and on trailing edge as possible to obtain maximum pressure.