Hi all!
I am looking for a way to rigoursly define the aero balance of my simulated aero kit:
The CFD is run to convergence with wall-resolved y+ of 2.5 average and 3.7 max, 350 iterations, and origin is at the intersection of the front axle, ground, and symmetery planes with x pointing rearwards and z pointing upwards.
Previously I was defining aero balance by integrating the quantity pressure * coords[:,0], then dividing by integrated pressure, then normalizing by wheelbase. However, I am not convinced that this is the correct way to find aero balance.
I am looking for a way to find the moment each surface element creates about the axis defined by the intersection of the front axle plane and the ground plane, such that I can find the distribution of force between the front and rear wheel.
I am attempting to do this currenly by finding the total traction in x and y per surface element, find the moment that each element creates, and then sum these moments to find the total moment about the front axle.
However, I cannot find a way to integrate surface_normal*pressure + wall shear stress as I don't see any variable that represents the surface normal of a surface element. And advice in how to integrate the dotproduct of the traction vector * distance vector would be welcomend! Additionally, if there is any easier way to calculate aero balance, that would be amazing.
