Abstract
In this paper, the structure of the external flow field around the wing of a Lobet Ganagobie light aircraft is investigated using CFD. A model has been developed to mimic the NACA 23012 geometry and then used to simulate the flow around the 3D aerofoil. A wind tunnel is used to collect new experimental data for lift coefficient to verify the accuracy of the model at Reynolds number, Re = 0.3 × 106. Then, the CFD model is utilised to produce velocity streamline plots and pressure and velocity contours at higher Re(2 × 106 − 3 × 106) to give a better understanding of the flow around the Lobet Ganagobie wing. The 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 warning device can be sensibly located.
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