[Airfoil]
Description1=Inverted NACA 2412
Thickness=0.12
NumberSets=1

[Set1]
Origin=NACA Report #824
Description1=Summary of Airfoil Data
Description2=Ira H Abbott, Albert E von Doenhoeff, and Louis S Stivers, Jr.
NumberPolars=3

[Set1-Polar1]
ReynoldsNumber=3000000
MachNumber=0.0
Description1=
NumberPoints=17
Clmax=1.59448000
AlphaClmax=15.281500
Value01= -20.437000 -1.133780 0.023242 0.097549
Value02= -18.246800 -1.208960 0.023242 0.062445
Value03= -16.312200 -1.509560 0.023242 0.028788
Value04= -15.796700 -1.565090 0.023242 0.025819
Value05= -15.281500 -1.594480 0.023242 0.025214
Value06= -14.220000 -1.527530 0.023242 0.023969
Value07= -12.064400 -1.398490 0.017611 0.022579
Value08= -10.004900 -1.243280 0.013562 0.031524
Value09= -7.976970 -1.043880 0.011257 0.040452
Value10= -5.851670 -0.855855 0.009099 0.038368
Value11= -3.757740 -0.648128 0.006785 0.036150
Value12= -1.663040 -0.456683 0.006374 0.041804
Value13= 0.174796 -0.245518 0.006370 0.042589
Value14= 2.303350 -0.047370 0.006920 0.044170
Value15= 4.207400 0.180351 0.007280 0.045032
Value16= 6.434330 0.375387 0.007984 0.047954
Value17= 8.436870 0.604937 0.009633 -0.047954

[Set1-Polar2]
ReynoldsNumber=6000000
MachNumber=0.0
Description1=
NumberPoints=25
Clmax=1.68592000
AlphaClmax=15.570400
Value01= -20.468800 -1.169740 0.018437 0.107796
Value02= -18.373200 -1.408290 0.018437 0.047962
Value03= -17.695600 -1.561820 0.018437 0.034969
Value04= -17.243800 -1.679390 0.018437 0.030077
Value05= -15.570400 -1.685920 0.018437 0.019216
Value06= -15.249000 -1.632040 0.018437 0.019874
Value07= -14.284000 -1.586310 0.018437 0.021852
Value08= -12.032200 -1.403390 0.014706 0.026958
Value09= -10.069300 -1.235110 0.011675 0.031439
Value10= -8.041370 -1.037340 0.009681 0.039239
Value11= -6.012680 -0.837866 0.007725 0.038621
Value12= -3.854350 -0.638312 0.007274 0.036524
Value13= -1.598480 -0.432133 0.006176 0.039857
Value14= 0.271638 -0.220958 0.006305 0.042648
Value15= 2.368120 -0.012972 0.006434 0.043822
Value16= 4.432960 0.170519 0.006670 0.042409
Value17= 6.370240 0.406535 0.007276 0.044679
Value18= 8.340340 0.619698 0.008219 0.045852
Value19= 10.537100 0.836232 0.009671 0.045622
Value20= 12.347100 1.023310 0.013023 0.027132
Value21= 13.251100 1.056140 0.013342 0.020079
Value22= 14.574600 1.085680 0.013342 0.009402
Value23= 15.573700 1.034790 0.013342 -0.001741
Value24= 16.377600 0.914980 0.013342 -0.010707
Value25= 18.601700 0.844414 0.013342 -0.057304

[Set1-Polar3]
ReynoldsNumber=9000000
MachNumber=0.0
Description1=
NumberPoints=11
Clmax=1.67939000
AlphaClmax=16.214000
Value01= -20.468000 -1.225300 0.018503 0.067223
Value02= -18.436200 -1.524260 0.018503 0.065030
Value03= -16.214000 -1.679390 0.018503 0.021229
Value04= -14.123100 -1.584680 0.018503 0.023331
Value05= -12.064200 -1.432790 0.014803 0.031384
Value06= -10.101400 -1.241640 0.011288 0.037252
Value07= -8.009150 -1.058590 0.009079 0.036899
Value08= -5.851650 -0.832960 0.007435 0.036224
Value09= -3.886540 -0.631768 0.007160 0.039071
Value10= 6.241710 0.440964 0.007057 0.045809
Value11= 8.308430 0.642660 0.007868 0.045905