airfoil geometry with flap
 

Hello. im working on a problem of this sort.iv picked up NACA0012 airfoil and truncated it at 70% of the chord length.at this iv created an edge and broken the airfoil into two parts.iv found the distance of separation between the two fragments that gives the maximum increment of cl(lift coefficient). the next part of it is causing me a problem.im trying to make the trailing edge fragment to act like a slotted flap and deflect it through a range of angles from 0 to 45 degrees on both clockwise and anticlockwise directions and show how the cl is affected by such rotation in addition to calculating the angle of deflection and on which direction when deflected the slotted flap acts as the best high lift device.im creating this geometry in gambit and solving it in fluent6.3. im facing a problem in creating the geometry.when im rotating the face of the trailing edge segment ( truncated part) through a certain angkle say iv tried for 40 degree..then the geometry no longer remains a 2d one..as one of the fragments is having a aprojection in the xz plane..because of which the mesh also is not getting exported as a 2d mesh as all nodes do not lie in the xy plane. please could anyone suggest me the proper method of creating the geometry properly in gambit so that it remains within the xy plane irrespective of the direction in which the flap is deflected. my summer project is in trouble due to this stage of the problem. please help me out. thanks.send reply on aeroanindita@gmail.com