North_roll(existent proper name would be nice)-
Normally airfoil data is in terms of 0 to 1 from olfactory organ to tail, with the Yu(pper) and Yl(ower) either given as shown,
or with Y +/-.
SolidWorks' convention in full general is that [+X is left], [+Y is upward], and [+Z if fwd].
So if y'all expect normal to the correct plane from the left, the origin is zero, with -Z going right, and +Y is to a higher place the Z axis
and -Y is beneath.
If you specify the olfactory organ of the airfoil at Z=0, the TE volition be at Z=-1
The Bend through XYZ are cartesian coords with the higher up SW convention.

Using the tool to draw an airfoil, you specify the Upper TE coord, progressing along the upper slant forrad.
In other words: (set X to zero for all coords and disregard)
For the airfoil coordinate pairs: Z starts at -1 and and the corresponding Y values increase from near zero to max upper camber and then Y values decrease to 0 as Z approaches 0 at the olfactory organ,
where ordinarily Z and Y=0.
Continuing on around below the nose, Z once again moves back toward the tail increasing(?-decreasing) to -1 once again,
while Y increases in the negative with a maximum value a maximum lower camber until it approaches near 0 once again.
A careful reading (many times?) of the above description and you should understand.

So converting the numbers from the ZA plans, the SW coords are as follows:
(Y'all could imagine those numbers as 10,Y on a standard graph from the parentheses),
but they take to be in the lodge they are below for the Curve thru XYZ to lay on the R Airplane.
Also, since your AF is non '1' long, you lot will starting time at Z=0 for the front rib rear and end at Z=499 for the front.
In the case of your numbers, assume 499 = 'one' for Z

Your Fwd rib becomes:
10 Y(vert) Z(horz)

0 -90 0
0 -89.5 100
0 -86 200
0 -77 300
0 -71 350
0 -61.8 400
0 -56 425
0 -49 450
0 0 499
0 49 475
0 71.5 450
0 87.vii 425
0 100 400
0 119 350
0 131.2 300
0 144 200
0 147 100
0 148.5 0

Study how the numbers are translated from the plans nautical chart.
Later the bend is generated, yous must 'projection' it on a sketch on the R airplane.
For the rear rib:
X= all cipher
Plans X=SW Z
Plans Y=SW Y, with upper = positive
and lower = negative
It takes about 1 infinitesimal to enter into Excel, just since it is not continuous, you MUST exercise a separate sldcrv for each curve.
(Don't forget to employ a metric template in SW)
Then:
Normal X,Y Y 10 Y X
SW Y,Z Y Z Y Z
0 148.v 0 0 -90 0
0 145 -100 0 -89.iii -100
0 137.5 -200 0 -84 -200
0 127 -300 0 -74 -300
0 114 -400 0 -30 -622
0 96.5 -500
0 77 -600
0 72 -622

The section specified equally direct appears negligible to me compared to the SW spline.
The SW file is available for written report hither: https://drive.google.com/file/d/1BG3...ew?usp=sharing
Y'all must pay attention to the operation of whether the numbers are positive or negative.
-Christian