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section_alpha_L0 is incorrect in output file "input_distributions.txt" when using non-linear airfoil properties.

Running the tests with python2.7 or python3, several of the test cases fail with the following warning in def _calc_segment_points():

pos = np.rot90(np.array([z_pos, y_pos, x_pos]), axes=(1, 0))
E       TypeError: rot90() got an unexpected keyword argument 'axes'

After some investigating, turns out the axes keyword is in the numpy v1.13 documentation, but not the numpy v1.11 documentation: relevant links:

v1.11
v1.13

v1.11 is my default for Linux Mint 18.

I was trying to recreate the wing as showcased in the research paper "Wing optimisation using Dual Number Automatic Differentiation in MachUp". That used a sweep table input file. MachUp reports it has read the file but the generated .stl is incorrect (It makes an stl but not with the specified sweep and it also uses grid 1 (when input.json specified grid100).
Is this option broken?
or am I doing things wrong?