[Techies]

Hi guys,
I don't know how to plot the chart of lift coefficient following the spanwise of an aeroplane wing. Has anyone done this before can help me ? Thanks a lot.

[aero_head]

In order to get the spanwise lift distribution, you have to create iso-surfaces at different spanwise locations of your choice. Generate xy plot for cp distribution (my addition: you'll need to create a UDF to calculate Cp, there are many threads out there too, like Pressure Coefficient in CFD-Post), then manually calculate the value of local Cl from excel or similar software (or write a UDF for Cl as well).

The catch is the data fluent will export will not have upper and lower surface separately, they will be mixed and you will have to manually find out which points lie on the upper surface and which on the lower. There will be no accompanying z coordinates to help you either. If you are going to extract data for a few geometries this will work, but if your work requires you to do it repeatedly for many geometries, I won't recommend this technique. In that case you should find some strategy to distinguish between upper and lower surfaces from the exported cp distribution data.

From: Spanwise Lift Distribution