Based on the excellent question and associated answers here, where the lift and drag forces on an airfoil are calculated, I am trying to modify the same approach to then solve the same problem on a cross-section derived from a CT image. This means that I don't have an analytical equation for the ...
@Alex Trounev Thanks, I must have missed that, could be that it is already there in the other question . Could be that I should delete the question as it gets close to a duplicate then..
I try again, could be there was a problem with copy paste from MMA to SE will check.
I see, the image changed its size upon being uploaded, I had a strange format which came from a CT scan so think something went wrong there. will check
I copied the image from MMA and it changed the format upon being uploaded. The code should run now, but with different dimensions
Hey thanks for this, I think I am getting the code by Tim Laska working now. the structure of his code is a bit different to mine.
To answer your question the mesh is not very nice, but I wanted to start with small poor resolution images before I go to high res stuff. This means that everything will be rough and poorly represented
The next thing I will do is to go for higher res, but first I need to get the different steps working on something small
I think I am working out what could be wrong, it seems like the mean in Tim Laska's code is not correct. I guess the idea of this is to calculate the middle of the elements and then calculate everything there. but it seems to be averaging the x with y in each coordinate and not x1 with x 2 .. maybe I am getting there. If it truly is a bug I will comment Tim's code
Discussion between Dunlop and Alex Tr…
Discussion between Dunlop and Alex Tr…