And here it goes a little contribution to the table saw blades gang:
I created a little program to perform the calculations for the table saw carving. As input, it takes the 4 digit NACA profile we want to carve, the size of the piece of wood (2x4, 2x6 for example) and the pitch angle. The output, as of today, is an eleven column list of numbers giving the (x,y) coordinates of the points of the airfoil, upper and lower curves, the next set of columns gives the (x,y) coordinates of the pitched airfoil, upper and lower, then the scaled to size pitched airfoils coordinates, and finally, the lest three columns gives the measures for setting the saw blade for the upper and lower foils.
I assumed a kerf of 1/8" but this could be easily changed to be part of the input.
Here is an example of the program runing for a NACA6616 (very similar to GOE222) airfoil on a 2x6 at 10 deg pitch:
NACA6616
wood dimensions:
+----------------+
wh | |
+----------------+
ww
wh=2.0
ww=6.0
Pitch angle(in deg)=10.0
0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 2.000000 0.158242
0.014756 0.035576 0.026911 -0.027387 0.050122 0.225587 0.187548 -0.133790 0.050122 1.774413 0.024452
0.033651 0.051116 0.049683 -0.035028 0.145579 0.337096 0.330063 -0.155210 0.145579 1.662904 0.003032
0.053323 0.063069 0.071677 -0.039371 0.249367 0.428221 0.464548 -0.157958 0.249367 1.571779 0.000284
0.073432 0.073003 0.093235 -0.041985 0.357835 0.507873 0.594655 -0.150941 0.357835 1.492127 0.007301
0.093836 0.081532 0.114498 -0.043482 0.469514 0.579524 0.721852 -0.137634 0.469514 1.420476 0.020608
0.114459 0.088972 0.135541 -0.044180 0.583621 0.644975 0.846923 -0.119835 0.583621 1.355025 0.038407
0.135252 0.095517 0.156415 -0.044273 0.699666 0.705311 0.970357 -0.098633 0.699666 1.294689 0.059609
0.156181 0.101294 0.177152 -0.043887 0.817314 0.761257 1.092489 -0.074749 0.817314 1.238743 0.083493
...
0.604355 0.120380 0.603978 -0.000393 3.445621 1.340977 3.569222 0.626957 3.445621 0.659023 0.785199
0.626088 0.117794 0.623912 0.001738 3.576730 1.348339 3.684789 0.660314 3.576730 0.651661 0.818556
0.647743 0.114778 0.643923 0.003647 3.707830 1.353082 3.801044 0.692443 3.707830 0.646918 0.850685
0.669317 0.111338 0.664016 0.005328 3.838888 1.355234 3.918019 0.723316 3.838888 0.644766 0.881558
0.690804 0.107480 0.684196 0.006778 3.969874 1.354821 4.035745 0.752908 3.969874 0.645179 0.911150
0.712201 0.103207 0.704465 0.007991 4.100758 1.351868 4.154250 0.781193 4.100758 0.648132 0.939435
0.733505 0.098524 0.724828 0.008963 4.231515 1.346395 4.273561 0.808150 4.231515 0.653605 0.966392
0.754711 0.093436 0.745289 0.009689 4.362119 1.338423 4.393704 0.833761 4.362119 0.661577 0.992003
0.775816 0.087945 0.765850 0.010167 4.492548 1.327968 4.514700 0.858006 4.492548 0.672032 1.016248
0.796817 0.082055 0.786516 0.010393 4.622778 1.315046 4.636572 0.880872 4.622778 0.684954 1.039114
0.817712 0.075769 0.807288 0.010364 4.752790 1.299671 4.759342 0.902344 4.752790 0.700329 1.060586
0.838496 0.069088 0.828170 0.010079 4.882565 1.281852 4.883027 0.922413 4.882565 0.718148 1.080655
0.859169 0.062016 0.849164 0.009534 5.012082 1.261598 5.007648 0.941070 5.012082 0.738402 1.099312
0.879725 0.054552 0.870274 0.008729 5.141324 1.238917 5.133222 0.958308 5.141324 0.761083 1.116550
0.900164 0.046699 0.891502 0.007663 5.270273 1.213810 5.259767 0.974124 5.270273 0.786190 1.132366
0.920481 0.038458 0.912852 0.006334 5.398912 1.186282 5.387301 0.988515 5.398912 0.813718 1.146757
0.940675 0.029828 0.934325 0.004742 5.527224 1.156330 5.515840 1.001483 5.527224 0.843670 1.159725
0.960741 0.020811 0.955925 0.002887 5.655191 1.123953 5.645403 1.013029 5.655191 0.876047 1.171270
0.980678 0.011405 0.977654 0.000770 5.782795 1.089146 5.776006 1.023158 5.782795 0.910854 1.181400
1.000482 0.001609 0.999517 -0.001609 5.910020 1.051901 5.907668 1.031878 5.910020 0.948099 1.190120And here is the code of the program: Feel free to use it, modify it and improve it, of course, there are no warranties, it certainly doesn't work and contains many errors.
airfoils.c (2.62 kB - downloaded 303 times.)
compile with
gcc airfoils.c -lm -o airfoils
run with
airfoils
Cheers,
Octavio