# Calculate spanwise lift and drag distribution

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 September 17, 2023, 04:10 Calculate spanwise lift and drag distribution #1 New Member   Hannes Join Date: Nov 2020 Posts: 2 Rep Power: 0 Greetings fellow CFD lovers and Tecplot experts, I am currently analyzing the flow around a three dimensional airfoil + flap configuration, using DLR TAU as the flow solver. I obtain the surface solution for both airfoil and flap, with multiple output variables, primarily c_p and c_f for my case. For my analysis, I want to plot the spanwise distribution of the lift and drag coefficients. From my understanding, that should be possible with the given surface solution and variables. I am using Tecplot for postprocessing, but also have access to Matlab if necessary. Any ideas on how to achieve that? That specific problem came up a few times in different forums, yet with no satisfactory answer. Thanks for any advice! Last edited by 35k; September 17, 2023 at 04:11. Reason: Typo

 September 21, 2023, 15:28 #2 Senior Member   Scott Fowler Join Date: May 2009 Posts: 112 Rep Power: 16 We have a Python script on our GitHub site which should accomplish what you want: https://github.com/Tecplot/handyscri...nts_VS_Span.py The script has some hard coded values between lines 234-257 that will need to be adjusted for your data. These values work with the OneraM6 dataset that is included in the 360 installation. This script requires PyTecplot, which in turn requires a Tecplot 360 license with active maintenance. The general idea is: 1) Compute Pressure XYZ components using the mesh normal direction 2) Extract a bunch of slices in the spanwise direction 3) Integrate the Pressure XYZ components for each slice 4) Create a new linear zone to store the integrated results vs. slice locations and plot the results If you have active maintenance you can also contact our suppor staff for more help. Scott