Main Article Content
This paper presents the computational design validation of a morphing wing profile that allows a change in the wing aspect ratio. Generally, the aerodynamic performance can be enhanced by changing the aspect ratio of the wing. Variable span morphing wing allows two distinct airfoil sections of the wing to extend its span using another section employing strap driven mechanism. The primary airfoil model section is maintained by NACA 4412 with span of 1.05 meters with full extension to 1.50 meters. Therefore, both two dimensional and three dimensional computational studies are carried out in a span morphed wing and un-morphed wing for various angles of attack respectively. It is found that the extended wing gives better aerodynamic performance and improved range. However, the separation phenomenon and turbulence occurs in the transition regions of wing profile. CFD FLUENT are used to understand the different flow patterns and pressure variations over the various sections of the wing. This study also demonstrates the potential effectiveness of a model meshing on the simulation and emphasizes the sensitivity of the solution outcome to the model solution setup.