We have tabulated spanwise data for the wing, in the form of cl0, cla, cm0 and cma with respect to spanwise position
eta. The aero data is provided for the flight shape, and is constructed without knowledge of the wing structure design,
with it being computed from CFD data.  We want to apply corrections to make these accurate on our wing in 2 stages;

1) match the data for a rigid aircraft
2) add a correction to account for flexibility

Our model has no twist by default, with the aerodynamic surfaces being flow-aligned. We can apply the polars to the
model on a strip-wise basis. If we take a Nastran case with this correction applied, and incline at the same angle of
attack, we find they don't match well. This is because the UVLM angle of attack does not vary exactly with the model
rigid angle of attack. For example for a case at -6 degree from nastran, the UVLM reports a spanwise variation between
-3 and -6 degrees, which results in an overprediction of lift and underprediction of moment. The first correction should
find the slope to account for this. This can be done by evaluating at two angles of attack and solving.

The second step involves computing a second twist correction (jig to flight, J2F). This correction accounts for the fact
that the previous analysis was done without structural deformation, however in reality, the deformation causes changes
in the local angles of attack and therefore aerodynamic forces. We do this by clamping the model at the root at two
angles of attack (here chosen as 0 and 1 degree); for these two cases, we aim to match the tabulated aerodynamic
coefficients by applying an additional twist FA2J and additionally a slope correction factor xi. This comes with the problem

F_data(1) - F_dlm(1) = A(1) * xi + B * FA2J
F_data(0) - F_dlm(0) = A(0) * xi + B * FA2J

where F_data is the tabulated aerodynamic data, F_dlm is the aerodynamic data from the deformed model, and matrices
A and B are the matrices that link the corrections to the forces. For these two cases, we can pose this as a linear
system and solve for FA2J and xi. Note that is the model is very stiff, this correction becomes trivial.