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GOE 14 AIRFOIL (goe14-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 14 AIRFOIL (goe14-il)
Reynolds number: 500,000
Max Cl/Cd: 93.89 at α=10°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe14-il-500000-n5.txt
Download as CSV file: xf-goe14-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 14 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2320   0.12558   0.12311  -0.0210   0.9077   0.0194
 -10.750  -0.2257   0.12304   0.12050  -0.0214   0.8869   0.0199
 -10.500  -0.2188   0.12024   0.11763  -0.0224   0.8708   0.0206
 -10.250  -0.2119   0.11736   0.11468  -0.0236   0.8570   0.0208
 -10.000  -0.2049   0.11454   0.11180  -0.0249   0.8445   0.0208
  -9.750  -0.1977   0.11173   0.10894  -0.0263   0.8326   0.0209
  -9.500  -0.1904   0.10893   0.10609  -0.0278   0.8220   0.0209
  -9.250  -0.1829   0.10615   0.10327  -0.0294   0.8114   0.0209
  -9.000  -0.1743   0.10330   0.10038  -0.0304   0.8021   0.0210
  -8.750  -0.1647   0.10065   0.09770  -0.0310   0.7925   0.0211
  -8.500  -0.1550   0.09818   0.09520  -0.0318   0.7834   0.0212
  -8.250  -0.1451   0.09582   0.09281  -0.0329   0.7737   0.0214
  -8.000  -0.1350   0.09346   0.09042  -0.0341   0.7651   0.0217
  -7.750  -0.1247   0.09104   0.08797  -0.0355   0.7559   0.0221
  -7.500  -0.1145   0.08853   0.08543  -0.0370   0.7472   0.0226
  -7.250  -0.1040   0.08592   0.08280  -0.0389   0.7376   0.0231
  -7.000  -0.0938   0.08327   0.08011  -0.0412   0.7288   0.0236
  -6.750  -0.0791   0.08025   0.07705  -0.0452   0.7193   0.0238
  -6.500  -0.0619   0.07715   0.07390  -0.0498   0.7104   0.0239
  -6.000  -0.0206   0.07073   0.06736  -0.0601   0.6896   0.0240
  -5.750  -0.0037   0.06784   0.06443  -0.0619   0.6776   0.0241
  -5.500   0.0138   0.06540   0.06194  -0.0633   0.6649   0.0243
  -5.250   0.0341   0.06300   0.05947  -0.0658   0.6509   0.0245
  -5.000   0.0564   0.06053   0.05691  -0.0687   0.6346   0.0247
  -4.750   0.0800   0.05806   0.05434  -0.0718   0.6162   0.0251
  -4.500   0.1048   0.05559   0.05175  -0.0749   0.5970   0.0256
  -4.250   0.1312   0.05307   0.04909  -0.0781   0.5779   0.0264
  -4.000   0.1656   0.04999   0.04582  -0.0833   0.5604   0.0272
  -3.750   0.1970   0.04727   0.04291  -0.0870   0.5447   0.0273
  -3.250   0.2479   0.04266   0.03807  -0.0906   0.5181   0.0276
  -3.000   0.2726   0.04092   0.03625  -0.0918   0.5066   0.0278
  -2.750   0.2997   0.03915   0.03435  -0.0933   0.4954   0.0281
  -2.500   0.3278   0.03737   0.03247  -0.0948   0.4855   0.0285
  -2.250   0.3562   0.03566   0.03061  -0.0961   0.4752   0.0291
  -1.750   0.4203   0.03076   0.02529  -0.0992   0.4576   0.0270
  -1.500   0.4471   0.02961   0.02407  -0.0998   0.4496   0.0280
  -1.250   0.4802   0.02711   0.02131  -0.1008   0.4423   0.0271
  -1.000   0.5080   0.02581   0.01988  -0.1012   0.4358   0.0270
  -0.750   0.5368   0.02441   0.01834  -0.1016   0.4294   0.0267
  -0.500   0.5661   0.02291   0.01665  -0.1019   0.4224   0.0267
  -0.250   0.5961   0.02113   0.01463  -0.1021   0.4164   0.0269
   0.000   0.6272   0.01857   0.01171  -0.1022   0.4101   0.0273
   0.250   0.6548   0.01799   0.01100  -0.1021   0.4032   0.0277
   0.500   0.6823   0.01768   0.01063  -0.1021   0.3974   0.0282
   0.750   0.7108   0.01681   0.00960  -0.1020   0.3915   0.0291
   1.000   0.7400   0.01250   0.00452  -0.1016   0.3868   0.0312
   1.250   0.7674   0.01243   0.00443  -0.1014   0.3813   0.0319
   1.500   0.7949   0.01233   0.00430  -0.1012   0.3755   0.0329
   1.750   0.8220   0.01223   0.00415  -0.1010   0.3694   0.0343
   2.000   0.8492   0.01221   0.00410  -0.1008   0.3638   0.0356
   2.250   0.8766   0.01218   0.00408  -0.1006   0.3576   0.0372
   2.500   0.9035   0.01220   0.00405  -0.1004   0.3510   0.0392
   2.750   0.9306   0.01226   0.00413  -0.1002   0.3453   0.0420
   3.000   0.9579   0.01241   0.00430  -0.1000   0.3395   0.0457
   3.500   1.0116   0.01280   0.00466  -0.0995   0.3269   0.0552
   3.750   1.0383   0.01296   0.00478  -0.0993   0.3199   0.0588
   4.000   1.0645   0.01310   0.00486  -0.0990   0.3139   0.0627
   4.250   1.0913   0.01328   0.00506  -0.0988   0.3086   0.0649
   4.500   1.1176   0.01344   0.00519  -0.0985   0.3028   0.0689
   4.750   1.1435   0.01365   0.00539  -0.0982   0.2971   0.0717
   5.000   1.1698   0.01374   0.00546  -0.0980   0.2915   0.0738
   5.250   1.1956   0.01385   0.00555  -0.0977   0.2858   0.0752
   5.500   1.2211   0.01399   0.00570  -0.0974   0.2807   0.0764
   5.750   1.2472   0.01410   0.00582  -0.0971   0.2762   0.0774
   6.000   1.2728   0.01424   0.00597  -0.0968   0.2714   0.0785
   6.250   1.2977   0.01445   0.00616  -0.0965   0.2666   0.0800
   6.500   1.3230   0.01463   0.00634  -0.0961   0.2620   0.0812
   6.750   1.3482   0.01481   0.00653  -0.0958   0.2569   0.0820
   7.000   1.3729   0.01501   0.00675  -0.0954   0.2525   0.0831
   7.250   1.3969   0.01527   0.00701  -0.0949   0.2485   0.0843
   7.500   1.4218   0.01546   0.00724  -0.0946   0.2449   0.0861
   7.750   1.4461   0.01569   0.00749  -0.0941   0.2405   0.0879
   8.000   1.4697   0.01596   0.00777  -0.0936   0.2368   0.0892
   8.250   1.4926   0.01627   0.00808  -0.0930   0.2332   0.0906
   8.500   1.5160   0.01654   0.00838  -0.0925   0.2304   0.0926
   8.750   1.5394   0.01679   0.00868  -0.0919   0.2274   0.0954
   9.000   1.5619   0.01709   0.00901  -0.0913   0.2241   0.0988
   9.250   1.5836   0.01743   0.00937  -0.0905   0.2207   0.1031
   9.500   1.6041   0.01782   0.00978  -0.0896   0.2172   0.1089
  10.000   1.6450   0.01752   0.01070  -0.0878   0.2110   1.0000
  10.250   1.6633   0.01794   0.01114  -0.0865   0.2065   1.0000
  10.500   1.6791   0.01850   0.01168  -0.0850   0.2015   1.0000
  10.750   1.6971   0.01895   0.01216  -0.0838   0.1967   1.0000
  11.000   1.7132   0.01952   0.01274  -0.0824   0.1903   1.0000
  11.250   1.7274   0.02022   0.01344  -0.0809   0.1845   1.0000
  11.500   1.7427   0.02087   0.01411  -0.0796   0.1773   1.0000
  11.750   1.7546   0.02176   0.01498  -0.0781   0.1689   1.0000
  12.000   1.7645   0.02283   0.01601  -0.0764   0.1583   1.0000
  12.250   1.7734   0.02401   0.01718  -0.0749   0.1479   1.0000
  12.500   1.7816   0.02530   0.01846  -0.0734   0.1403   1.0000
  13.000   1.7957   0.02822   0.02140  -0.0706   0.1288   1.0000
  13.250   1.8005   0.02996   0.02317  -0.0693   0.1235   1.0000
  13.500   1.8044   0.03183   0.02506  -0.0681   0.1189   1.0000
  13.750   1.8092   0.03367   0.02696  -0.0671   0.1151   1.0000
  14.000   1.8124   0.03572   0.02907  -0.0661   0.1120   1.0000
  14.250   1.8134   0.03804   0.03144  -0.0652   0.1093   1.0000
  14.500   1.8156   0.04031   0.03379  -0.0644   0.1071   1.0000
  14.750   1.8186   0.04254   0.03611  -0.0638   0.1049   1.0000
  15.000   1.8187   0.04511   0.03876  -0.0633   0.1024   1.0000
  15.250   1.8160   0.04810   0.04183  -0.0629   0.0998   1.0000
  15.500   1.8101   0.05158   0.04537  -0.0626   0.0973   1.0000
  15.750   1.8060   0.05495   0.04883  -0.0626   0.0953   1.0000
  16.000   1.8042   0.05812   0.05211  -0.0626   0.0928   1.0000
  16.250   1.7988   0.06184   0.05592  -0.0628   0.0899   1.0000
  16.500   1.7888   0.06622   0.06038  -0.0632   0.0868   1.0000
  16.750   1.7787   0.07067   0.06492  -0.0638   0.0842   1.0000
  17.000   1.7685   0.07519   0.06953  -0.0644   0.0799   1.0000
  17.250   1.7515   0.08073   0.07512  -0.0653   0.0752   1.0000
  17.500   1.7339   0.08640   0.08086  -0.0664   0.0702   1.0000
  17.750   1.7144   0.09245   0.08698  -0.0677   0.0660   1.0000
  18.000   1.6954   0.09851   0.09311  -0.0692   0.0620   1.0000
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