Aerodynamic Analysis of a Simple Folding Rectangular Wing at Different Cant Angles

Abstract This paper investigates the aerodynamic effects of varying the cant angle of a simple folding rectangular wing with a NACA2412 cross section. Four different cant angles have been considered at four different Reynolds numbers for this study, taking three values for aspect ratio at three angles of attack. Lift, drag and rolling moment have been measured for each configuration. Measurements have first been done via CFD using Ansys Fluent software platform and then experimentally in a wind tunnel, followed by graphical comparison of the studies. Results reveal that the 60° and 30° cant angles overall produce a higher rolling moment at a lower angle of attack, while the base wing produces a lower rolling moment and a lower drag. At a high angle of attack, the base wing produces a higher rolling moment as well as a higher drag. This method provides an alternative to conventional ailerons currently used in most aircraft.