I've been working on a project that required generating Riblett airfoils again, and yet again I ended up writing a simple perl script to help. I've attached that script in case its useful to others; I'll probably update it occasionally, mostly to add more features for my own use. Be aware: All values are typed in by me, with little double checking, so be careful and let me know about any errors!
In its simplest form, you can run the script as, for example, ./riblett.pl 35A315. If you do, you'll see output like this:
I also support a bit more flexibility in cambers and widths. Cambers between 0 and GA-6 are interpolated; for non-integral cambers, use brackets. Arbitrary thicknesses are supported; for non-integral thicknesses, use brackets. So ./riblett.pl 35A[2.5][14.5] is valid.
I support a single option at this point -- if sharp is specified on the command line, the coordinates are tweaked to make the trailing edge perfectly sharp. Some but not all Riblett thickness distributions have this property, and it's pretty important for comparing different airfoils in, for example, XFoil.
Speaking of XFoil, if output files are specified on the command line, data of the appropriate format is written to that file. I currently support .txt (human-readable table), .dat (XFoil-style), and .dxf (for Rhino import, etc). Pulling it all together, then, you might try something like this: ./riblett.pl 37A3[14.5] sharp /tmp/out.dat /tmp/out.dxf.
Let me know if this is useful to you guys, and if there's any other features that you'd like to see added. As mentioned, I'll probably be fiddling with it for a bit, so good time to ask!
View attachment 37410
In its simplest form, you can run the script as, for example, ./riblett.pl 35A315. If you do, you'll see output like this:
Code:
Series: 35
Cusp: no (A)
Camber: 3 (design CL 0.3)
Thickness: 15%
Options: none
35A315
Sta upper lower
0.00 0.000 0.000
0.25 0.938 -0.812
0.50 1.323 -1.083
0.75 1.618 -1.278
1.25 2.119 -1.569
2.50 3.079 -2.079
5.00 4.470 -2.766
7.50 5.500 -3.264
10.00 6.332 -3.662
15.00 7.625 -4.259
20.00 8.577 -4.661
25.00 9.264 -4.918
30.00 9.724 -5.044
35.00 9.953 -5.039
40.00 9.959 -4.911
45.00 9.758 -4.672
50.00 9.357 -4.359
55.00 8.755 -4.019
60.00 7.998 -3.642
65.00 7.120 -3.226
70.00 6.152 -2.784
75.00 5.135 -2.327
80.00 4.114 -1.868
85.00 3.095 -1.409
90.00 2.074 -0.950
95.00 1.053 -0.491
100.00 0.032 -0.032
I also support a bit more flexibility in cambers and widths. Cambers between 0 and GA-6 are interpolated; for non-integral cambers, use brackets. Arbitrary thicknesses are supported; for non-integral thicknesses, use brackets. So ./riblett.pl 35A[2.5][14.5] is valid.
I support a single option at this point -- if sharp is specified on the command line, the coordinates are tweaked to make the trailing edge perfectly sharp. Some but not all Riblett thickness distributions have this property, and it's pretty important for comparing different airfoils in, for example, XFoil.
Speaking of XFoil, if output files are specified on the command line, data of the appropriate format is written to that file. I currently support .txt (human-readable table), .dat (XFoil-style), and .dxf (for Rhino import, etc). Pulling it all together, then, you might try something like this: ./riblett.pl 37A3[14.5] sharp /tmp/out.dat /tmp/out.dxf.
Code:
Series: 37
Cusp: no (A)
Camber: 3 (design CL 0.3)
Thickness: 14.5%
Options: sharp
Writing to /tmp/out.dat...
Writing to /tmp/out.dxf...
Let me know if this is useful to you guys, and if there's any other features that you'd like to see added. As mentioned, I'll probably be fiddling with it for a bit, so good time to ask!
View attachment 37410
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