Plotting Spanwise Lift Distribution from Surface Cp Data on a Wing
 

Hi,

I have a 3D plot of the surface pressure coefficient over a wing and I want to plot the spanwise lift distribution.

The strategy I have in mind is to extract a discrete number of slices along the span (e.g. 100) and use these zones to perform scalar integration. Once this is done, I can plot the result obtained at each spanwise station versus the y-coordinate of the spanwise station to obtain the spanwise lift distribution.

However, I'm currently running into two problems:

(1) I'm uncertain whether I am performing the integration correctly as I'm still new to this function. I'm selecting scalar integration of Cp, integrating by Zones and selecting the zones corresponding to the spanwise slices, and integrating over J Lines. Is this correct?

(2) I don't know how to obtain the y-coordinates of the spanwise stations as a variable that I can use to plot versus my result.

If anyone can help me with any of these problems, or if you have a better idea as to how to approach this problem, please let me know!

Thanks in advance!

Update
 

In case anyone was wondering, I was not able to find a way to do this. I also posted my question on a tecplot360 youtube video, and was notified that plotting the spanwise lift distribution is something tecplot is not yet capable of. On the bright side, they are considering introducing a macro that would be able to do this in the future.

In the meantime, I simply extracted 100 slices and exported the data files into MATLAB where I created the plots manually.

yes, I am also not able to do it in TECPLOT