Airfoil design has come a long way since the '20s. I HAD been planning to use the NLF(1)-0115 airfoil, computer designed in 1995 by a team of aerodynamicists on contract to Langley Research Center. But now another airfoil has been designed specifically for the KR2S, the AS504x. It is quite similar, but optimized for the lower Reynolds numbers that the KR flies at, and therefore more efficient than the NLF would be for our application. KRNet raised over $1000 to fund wind tunnel testing of this airfoil at the University of Illinois' wind tunnel.

But just in case you're still interested in the NLF, details are listed below.

This is a plot of the characteristics of the NLF(1)-0115. This airfoil is detailed in the July/August 95 issue of the AAIA's Journal of Aircraft. Coordinates are listed below.

 NLF(1)-0115 coordinates:
     x    y
 1.00000  0.00000
 0.99614  0.00060
 0.98507  0.00282
 0.96792  0.00704
 0.94579  0.01293
 0.91933  0.01975
 0.88867  0.02685
 0.85376  0.03411
 0.81494  0.04170
 0.77287  0.04961
 0.72820  0.05769
 0.68161  0.06575
 0.63378  0.07350
 0.58540  0.08060
 0.53711  0.08650
 0.48908  0.09046
 0.44103  0.09238
 0.39307  0.09269
 0.34578  0.09170
 0.29969  0.08957
 0.25536  0.08643
 0.21335  0.08239
 0.17420  0.07751
 0.13842  0.07180
 0.10644  0.06522
 0.07855  0.05773
 0.05494  0.04928
 0.03560  0.03993
 0.02048  0.02992
 0.00954  0.01957
 0.00270  0.00940
 0.00000  0.00012

 0.00252 -0.00715
 0.01126 -0.01302
 0.02600 -0.01859
 0.04634 -0.02384
 0.07192 -0.02889
 0.10230 -0.03376
 0.13698 -0.03841
 0.17547 -0.04279
 0.21723 -0.04681
 0.26171 -0.05036
 0.30835 -0.05333
 0.35657 -0.05558
 0.40578 -0.05698
 0.45539 -0.05733
 0.50482 -0.05642
 0.55345 -0.05373
 0.60155 -0.04844
 0.65013 -0.04101
 0.69911 -0.03297
 0.74738 -0.02532
 0.79388 -0.01850
 0.83761 -0.01278
 0.87762 -0.00828
 0.91305 -0.00497
 0.94313 -0.00274
 0.96722 -0.00133
 0.98498 -0.00042
 0.99613 -0.00004
 1.00000  0.00000

Return to Mark Langford's opinions