XFOIL Blended Airfoil Ordinates

XFOIL is an interactive program for the design and analysis of subsonic isolated airfoils. You can download the program for free here:

http://web.mit.edu/drela/Public/web/xfoil/

The airfoil ordinates developed in an earlier post were imported into the program and smoothed for analysis. Listed below is the set of smoothed ordinates for the GN-1 Aircamper airfoil exported from XFOIL.

Station Ordinate

1.000000 0.000000 Trailing Edge
0.995458 0.002617
0.985912 0.004412
0.973799 0.006650
0.959737 0.009487
0.945087 0.012411
0.931205 0.015248
0.918239 0.017484
0.905565 0.020025
0.892297 0.022460
0.878142 0.024934
0.863962 0.027360
0.850022 0.030137
0.836368 0.033145
0.823039 0.035827
0.809479 0.038974
0.795025 0.042144
0.780086 0.045437
0.765333 0.048731
0.751259 0.052049
0.738329 0.054578
0.725063 0.056931
0.710941 0.059771
0.696988 0.062622
0.683810 0.064975
0.670980 0.067389
0.657872 0.069677
0.643413 0.071704
0.628784 0.073968
0.614423 0.076145
0.600793 0.077814
0.587284 0.079823
0.573197 0.081621
0.558362 0.083107
0.543550 0.084621
0.529738 0.085882
0.516418 0.086943
0.502864 0.088254
0.488469 0.089318
0.473897 0.090295
0.459318 0.091324
0.444603 0.092324
0.430040 0.093058
0.415755 0.093947
0.400947 0.094484
0.385791 0.094816
0.370599 0.095003
0.355583 0.095108
0.340917 0.094947
0.327098 0.094818
0.314110 0.094200
0.301045 0.093836
0.287482 0.093208
0.273490 0.092509
0.259287 0.091452
0.244656 0.090365
0.229684 0.089036
0.214571 0.087695
0.200100 0.086078
0.185700 0.084244
0.171981 0.082222
0.158938 0.079673
0.146567 0.077330
0.134939 0.074470
0.122274 0.070638
0.109174 0.066541
0.096151 0.061788
0.083023 0.056509
0.071195 0.050981
0.058951 0.044323
0.046658 0.037427
0.035322 0.030658
0.025649 0.024600
0.018679 0.019902
0.013693 0.016249
0.009812 0.013557
0.006855 0.011425
0.004770 0.009292
0.002991 0.007376
0.001684 0.005514
0.000891 0.003505
0.000272 0.001669
0.000000 -0.000000 Leading Edge
0.000173 -0.001728
0.000538 -0.003644
0.001204 -0.005625
0.002625 -0.007538
0.004564 -0.009519
0.006998 -0.011641
0.010068 -0.013705
0.014217 -0.015353
0.019770 -0.016842
0.026835 -0.017986
0.036264 -0.018552
0.048253 -0.018997
0.061042 -0.019644
0.074066 -0.019970
0.087424 -0.020641
0.101523 -0.020989
0.116385 -0.020974
0.130914 -0.021020
0.144181 -0.020818
0.157469 -0.020118
0.170648 -0.019361
0.183733 -0.018452
0.197259 -0.017715
0.211833 -0.016576
0.227231 -0.015433
0.242874 -0.014262
0.258414 -0.013071
0.273674 -0.011918
0.288368 -0.010907
0.303392 -0.010190
0.318757 -0.009422
0.333827 -0.008644
0.348762 -0.008213
0.364235 -0.008019
0.379602 -0.007794
0.395040 -0.007403
0.410408 -0.007004
0.425403 -0.006780
0.440444 -0.006810
0.455780 -0.006887
0.471219 -0.006888
0.486270 -0.006863
0.500485 -0.007015
0.514560 -0.007298
0.528756 -0.007570
0.543152 -0.007815
0.558013 -0.008128
0.573517 -0.008522
0.589137 -0.008918
0.604395 -0.009248
0.619648 -0.009435
0.634893 -0.009519
0.650464 -0.009505
0.665926 -0.009506
0.681317 -0.009282
0.697116 -0.008918
0.713133 -0.008545
0.729139 -0.008174
0.745152 -0.007801
0.761181 -0.007427
0.777211 -0.007054
0.793241 -0.006681
0.809272 -0.006308
0.825302 -0.005935
0.841329 -0.005561
0.857353 -0.005189
0.873370 -0.004816
0.889354 -0.004441
0.905287 -0.004076
0.921158 -0.003714
0.936706 -0.003312
0.951585 -0.002972
0.965834 -0.002804
0.978600 -0.002431
0.988583 -0.001875
0.996204 -0.002120
1.000000 0.000000 Trailing Edge