cover all the main physical features of the movement of the aircraft or aircraft component an airfoil in this case through the fluid u03b1 13 values u2212 3 00 u2212 2 50 u2212 2 00 u2212 1 50 u2212 1 00 u2212 0 50 0 00 0 50 1 00 1 50 2 00 2 50 3 00 m 9 values 0 40 0 45 0 50 0 55 0 60 0 65 0 70 0 75 0 80 u03b4 9 values u2212 5 00 u2212 3 00 u2212 2 00 u2212 1 00 0 00 1 00 2 00 3 00 5 00 u03b1 9 values u2212 3 00 u2212 2 50 u2212 1 50 u2212 1 00 0 00 1 00 1 50 2 50 3 00 in step 23 the lift coefficient 13 the drag coefficient 15 the pitching moment coefficient 17 and the surface pressure on the airfoil 11 for each selected case are calculated by a computational fluid dynamic software program cfd rans as it can be seen in fig3 there are big differences in the flow field nature in the four cases shown with different values of the parameters u03b1 u03b4 and m that impose very different aerodynamic forces in the airfoil 11 in step 25 the results of said calculation are stored in a database not only global force coefficients and pressure distribution but also the.