Refine Aerodynamic Mesh

[x] should also write a test for when the #structural panels exceeds the #aerodynamic panels, for both linear and cosine.
[x] Added functionality to interpolate geometric input
[x] Now interpolates both LE and TE
[x] pytested

Remarks

User MUST define input from Left-to-Right
User MUST define aerodynamic input, and thus the sections, perpendicular to the 1/4c line, otherwise accuracy suffers..

Elliptical wing

[x] Resolved geometric problem by calculating new sections using the 1/4c line as a starting base. From there using weights and average chords the new LE and TE is calculated, this preserves the original orientation of the sections, within the newly refined sections.
[x] Converges now, big bug in that one has to remove the wake each time one resets the va
[x] Can one also update the existing filaments, instead of relying on a function that removes them?
[x] Double check the AR calculation input
[x] Get AR = 3 case to converge well
[x] Check with old thesis script, to see how close you are
[x] Pytested both the input and output that is create_geometry_general and output_results functions, so the error MUST be within the solve_lifting_line_system_matrix_approach_art_visc function .

Next-step

[x] Start with pytesting AIC matrix
[x] Isolate the whole solve_lifting_line_system_matrix_approach_art_visc function and write a proper pytest for it
[x] Changing reference frame to ENU, was implemented
[x] Step by step comparison was done with old codd
[x] the correct difference between AR 3 and AR 20 shows in CL
[x] CD does not match yet, need to resolve this.
[x] once matching, write pytest