Volume : 4, Issue : 4, April - 2015

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

Hardik S. Patel

Abstract :

<p>&nbsp;The present study comprises steady state, two&ndash;dimensional computational investigations performed on NACA0012&nbsp;</p> <div>(National advisory committee for aeronautics) airfoil to analyse the effect of pressure difference on airfoil with GF (gurney&nbsp;</div> <div>flap) at various angle of attack using viscous&ndash;laminar model of FLUENT &amp; using CAD preparation of two dimensional&nbsp;</div> <div>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&nbsp;</div> <div>16?. Static pressure distribution on the airfoil surface is present. From computational investigation, it is recommended that Gurney flaps with a&nbsp;</div> <div>approximately height of 4% chord to be installed perpendicular to chord and on trailing edge as possible to obtain maximum pressure.</div>