CFD Results

Early Results

CFD Results using ANSYS Fluent Solver

The results below represent the work done in ANSYS on the A320 wing with and without a winglet. The first four figures represent mach, and velocity path-lines over the wing without a winglet. In Figure 1 it can be seen that the initial mach of .17 slows when it initially hits the wing and then speeds up as it goes over the top of the wing. Figure 2 shows the turbulence coming off of the wingtip although it must be mentioned that the velocity values are much higher than they should be and needs to be fixed. The final Figure 3 shows the static pressure contour over the airfoil. This shows the lower pressure above the wing that creates lift.

Figure 1. Representation of the mach number over the A320 wing without a winglet, top and side views.

Figure 2. Velocity path lines showing the air speed over the wing and vorticies from the wingtip.

Figure 3. Pressure contour of the A320 wing showing lower pressure above the wing creating lift

A320 Wing with Blended winglet

The wing with the blended winglet was simulated with the same parameters as the wing without a winglet. Below shows the changes in mach over the wing along with the calculated lift and drag values. These don't match with our reference paper and are much lower than the correct values. This could be due to issues in our meshing or boundary conditions. Despite the issues, the changes in mach seem to be correct and are are shown. From Figure 4 it can be seen that the mach stays around .17 which is consistent with our velocity of 60 m/s. Although there are issues in the simulation it is interesting that the mach number calculations seem to be correct and the mach pathlines also show an interesting change in the flow from the wingtip. The blended winglet pulls the turbulent flow up and away from the top of the wing which can reduce drag.

Figure 4. Path lines showing the change in mach number over the wing and blended winglet.

Final Results

Lift Coefficient vs Angle of Attack

Drag Coefficient vs Angle of Attack

CL/CD vs Angle of Attack

CL/CD

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