Computational Study of aerodynamic performance and flow structure around NACA 23012 wing

The structure of the external flow field around the wing of a Lobet Ganagobie light aircraft is investigated in this paper by using Computational Fluid Dynamics method (CFD). A model has been developed to mimic the NACA 23012 geometry and used to simulate the flow around it. A wind tunnel is used to collect new experimental data for lift coefficient to verify the accuracy of the model at Reynolds numbers, Re = 0.3 x 106. Then, the CFD model is utilised to produce velocity streamline plots and pressure and velocity contours at hiher Re number (2 xl06 3 x 106) to have a better understanding of the flow around Lobet Ganagobie wing model. rnThe turbulence model is selected based on the comparison of experimental data with results from different CFD models. Driven by the abrupt stalling characteristics of the NACA 23012 airfoil section, the model is used to predict the position of the stagnation point on the airfoil so that a stall waning device can be sensibly located