Add out-of-plane contributions
The load matrix is currently computed by using the normal forces in the z
direction only. This is not general at all: the direction is hardcoded and the wing might not even be parallel to only one direction.
The load matrix should be computed as,
Q = W^T N
,
where W
(resp. N
) would contain the displacements (resp. the normal forces) for each nodes along x
, y
, z
on each column, and for each mode on its row. Example W
for 3 nodes in 2D (x
and y
) and 2 modes:
W = [w_1_x^{1} w_1_x^{2};
w_1_y^{1} w_1_y^{2};
w_2_x^{1} w_2_x^{2};
w_2_y^{1} w_2_y^{2};
w_3_x^{1} w_3_x^{2};
w_3_y^{1} w_3_y^{2}]