4 Attachment(s)
Using Curve through XYZ Points
Attachment 8496
rkirk77-
Very simple: Use Excel and arrange the X coords along Z in SW and the Y coords along Y and set 0 for all the X coords.
You can find most airfoils in this DB: https://m-selig.ae.illinois.edu/ads/coord_database.html
- The file format must be a three-column, tab, or space-delimited list of only X, Y, and Z coordinates. Do not include any column headings, such as X, Y, and Z or other extraneous data.
Save it as a .txt or .sldcrv file type.
Use 0 to 1 or 0 to 100 so it should look like this-ish:
0 0 0
0 .25 -.1
0 .375 -.2
0 .4 -.3
...
0 .2 -.9
0 .1 -.95
0 0 -1
This will give you a nice airfoil on the right plane with the nose fwd in the +Z direction
Your actual data from the above site:
NACA 23012 12%
1.00003 0.00126
0.99730 0.00170
0.98914 0.00302
0.97563 0.00518
0.95693 0.00812
0.93324 0.01176
0.90482 0.01602
0.87197 0.02079
0.83506 0.02597
0.79449 0.03145
0.75070 0.03712
0.70417 0.04285
0.65541 0.04854
0.60496 0.05405
0.55335 0.05924
0.50117 0.06397
0.44897 0.06811
0.39733 0.07150
0.34681 0.07402
0.29796 0.07554
0.25131 0.07597
0.20738 0.07524
0.16604 0.07320
0.12732 0.06915
0.09230 0.06265
0.06203 0.05382
0.03730 0.04324
0.01865 0.03176
0.00628 0.02030
0.00015 0.00956
0.00000 0.00000
0.00533 -0.00792
0.01557 -0.01401
0.03029 -0.01870
0.04915 -0.02248
0.07195 -0.02586
0.09868 -0.02922
0.12954 -0.03282
0.16483 -0.03660
0.20483 -0.04016
0.24869 -0.04283
0.29531 -0.04446
0.34418 -0.04510
0.39476 -0.04482
0.44650 -0.04371
0.49883 -0.04188
0.55117 -0.03945
0.60296 -0.03655
0.65360 -0.03327
0.70257 -0.02975
0.74930 -0.02607
0.79330 -0.02235
0.83407 -0.01866
0.87118 -0.01512
0.90420 -0.01180
0.93279 -0.00880
0.95661 -0.00621
0.97543 -0.00410
0.98901 -0.00254
0.99722 -0.00158
0.99997 -0.00126
Which I copy/pasted to notepad and saved.
Then imported to Excel and with a little wizardry becomes:
x0 |
y |
z(x) |
0 |
0.00126 |
-1.00003 |
0 |
0.0017 |
-0.9973 |
0 |
0.00302 |
-0.98914 |
0 |
0.00518 |
-0.97563 |
0 |
0.00812 |
-0.95693 |
0 |
0.01176 |
-0.93324 |
0 |
0.01602 |
-0.90482 |
0 |
0.02079 |
-0.87197 |
0 |
0.02597 |
-0.83506 |
0 |
0.03145 |
-0.79449 |
0 |
0.03712 |
-0.7507 |
0 |
0.04285 |
-0.70417 |
0 |
0.04854 |
-0.65541 |
0 |
0.05405 |
-0.60496 |
0 |
0.05924 |
-0.55335 |
0 |
0.06397 |
-0.50117 |
0 |
0.06811 |
-0.44897 |
0 |
0.0715 |
-0.39733 |
0 |
0.07402 |
-0.34681 |
0 |
0.07554 |
-0.29796 |
0 |
0.07597 |
-0.25131 |
0 |
0.07524 |
-0.20738 |
0 |
0.0732 |
-0.16604 |
0 |
0.06915 |
-0.12732 |
0 |
0.06265 |
-0.0923 |
0 |
0.05382 |
-0.06203 |
0 |
0.04324 |
-0.0373 |
0 |
0.03176 |
-0.01865 |
0 |
0.0203 |
-0.00628 |
0 |
0.00956 |
-0.00015 |
0 |
0 |
0 |
0 |
-0.00792 |
-0.00533 |
0 |
-0.01401 |
-0.01557 |
0 |
-0.0187 |
-0.03029 |
0 |
-0.02248 |
-0.04915 |
0 |
-0.02586 |
-0.07195 |
0 |
-0.02922 |
-0.09868 |
0 |
-0.03282 |
-0.12954 |
0 |
-0.0366 |
-0.16483 |
0 |
-0.04016 |
-0.20483 |
0 |
-0.04283 |
-0.24869 |
0 |
-0.04446 |
-0.29531 |
0 |
-0.0451 |
-0.34418 |
0 |
-0.04482 |
-0.39476 |
0 |
-0.04371 |
-0.4465 |
0 |
-0.04188 |
-0.49883 |
0 |
-0.03945 |
-0.55117 |
0 |
-0.03655 |
-0.60296 |
0 |
-0.03327 |
-0.6536 |
0 |
-0.02975 |
-0.70257 |
0 |
-0.02607 |
-0.7493 |
0 |
-0.02235 |
-0.7933 |
0 |
-0.01866 |
-0.83407 |
0 |
-0.01512 |
-0.87118 |
0 |
-0.0118 |
-0.9042 |
0 |
-0.0088 |
-0.93279 |
0 |
-0.00621 |
-0.95661 |
0 |
-0.0041 |
-0.97543 |
0 |
-0.00254 |
-0.98901 |
0 |
-0.00158 |
-0.99722 |
0 |
-0.00126 |
-0.99997 |
Copy paste into notepad and lose the header.
Use the 'Curve through XYZ Points' tool.
Browse for your NACA 23012.sldcrv file you saved from notepad.
Import and you get a nice spline.
Insert a sketch on the R plane and project the imported spline.
Cap with a nice line at the tail.
Now it is 1" long; either scale the sketch or extrude it .1" to a solid,
and then scale the solid.
You can do a root version chord length and a tip version chord length, and
even introduce washout (twist) and then loft for a complex wing including sweep.
Easy peasy.
'-)
-Christian
Attachment 8496
Attachment 8497
Attachment 8498
Part and data files:
Attachment 8499
Using Curve through XYZ Points
North_roll(real name would be nice)-
Normally airfoil data is in terms of 0 to 1 from nose to tail, with the Yu(pper) and Yl(ower) either given as shown,
or with Y +/-.
SolidWorks' convention in general is that [+X is left], [+Y is up], and [+Z if fwd].
So if you look normal to the right plane from the left, the origin is zero, with -Z going right, and +Y is above the Z axis
and -Y is below.
If you specify the nose of the airfoil at Z=0, the TE will be at Z=-1
The Curve through XYZ are cartesian coords with the above SW convention.
Using the tool to draw an airfoil, you specify the Upper TE coord, progressing along the upper camber forward.
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 nose,
where normally Z and Y=0.
Continuing on around below the nose, Z again moves back toward the tail increasing(?-decreasing) to -1 again,
while Y increases in the negative with a maximum value a maximum lower camber until it approaches near 0 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:
(You could imagine those numbers as X,Y on a standard graph from the parentheses),
but they have to be in the order they are below for the Curve thru XYZ to lay on the R Plane.
Also, since your AF is not '1' long, you will start at Z=0 for the front rib rear and end at Z=499 for the front.
In the case of your numbers, assume 499 = '1' for Z
Your Fwd rib becomes:
X 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 |
87.7 |
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 chart.
After the curve is generated, you must 'project' it on a sketch on the R plane.
For the rear rib:
X= all zero
Plans X=SW Z
Plans Y=SW Y, with upper = positive
and lower = negative
It takes about 1 minute to enter into Excel, but since it is not continuous, you MUST do a separate sldcrv for each curve.
(Don't forget to use a metric template in SW)
So:
Normal X,Y |
Y |
X |
|
Y |
X |
SW Y,Z |
Y |
Z |
|
Y |
Z |
0 |
148.5 |
0 |
0 |
-90 |
0 |
0 |
145 |
-100 |
0 |
-89.3 |
-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 as straight appears negligible to me compared to the SW spline.
The SW file is available for study here: https://drive.google.com/file/d/1BG3...ew?usp=sharing
You must pay attention to the operation of whether the numbers are positive or negative.
-Christian