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GOE 420 AIRFOIL (goe420-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 420 AIRFOIL (goe420-il)
Reynolds number: 100,000
Max Cl/Cd: 32.68 at α=11.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe420-il-100000.txt
Download as CSV file: xf-goe420-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 420 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2676   0.12366   0.11884  -0.0561   0.9770   0.1698
 -10.000  -0.5954   0.06687   0.06138  -0.0900   0.9591   0.0938
  -9.750  -0.6038   0.06216   0.05643  -0.0921   0.9514   0.0934
  -9.500  -0.6184   0.05878   0.05285  -0.0908   0.9420   0.0930
  -9.250  -0.6196   0.05464   0.04834  -0.0918   0.9349   0.0928
  -9.000  -0.6248   0.05176   0.04515  -0.0900   0.9263   0.0926
  -8.750  -0.6191   0.04873   0.04173  -0.0897   0.9191   0.0926
  -8.500  -0.5986   0.04576   0.03827  -0.0912   0.9150   0.0931
  -8.250  -0.6043   0.04440   0.03666  -0.0872   0.9061   0.0934
  -8.000  -0.5852   0.04238   0.03426  -0.0872   0.9004   0.0943
  -7.750  -0.5484   0.04088   0.03280  -0.0896   0.8968   0.0968
  -7.500  -0.5443   0.04023   0.03208  -0.0865   0.8890   0.0982
  -7.250  -0.5238   0.03917   0.03084  -0.0860   0.8830   0.1005
  -7.000  -0.4905   0.03779   0.02912  -0.0874   0.8788   0.1034
  -6.750  -0.4693   0.03686   0.02820  -0.0868   0.8730   0.1058
  -6.500  -0.4558   0.03633   0.02770  -0.0849   0.8652   0.1084
  -6.250  -0.4188   0.03533   0.02651  -0.0865   0.8601   0.1140
  -6.000  -0.3723   0.03430   0.02560  -0.0897   0.8565   0.1224
  -5.750  -0.3751   0.03415   0.02529  -0.0849   0.8447   0.1268
  -5.500  -0.3360   0.03312   0.02434  -0.0868   0.8400   0.1395
  -5.250  -0.2920   0.03183   0.02331  -0.0895   0.8370   0.1624
  -5.000  -0.3037   0.03191   0.02346  -0.0837   0.8251   0.1733
  -4.750  -0.2697   0.03100   0.02284  -0.0848   0.8205   0.2190
  -4.500  -0.2252   0.03080   0.02277  -0.0874   0.8175   0.2655
  -4.250  -0.2345   0.03143   0.02344  -0.0818   0.8052   0.2777
  -4.000  -0.1958   0.03140   0.02333  -0.0833   0.8008   0.3086
  -3.750  -0.1496   0.03135   0.02337  -0.0857   0.7980   0.3364
  -3.500  -0.1590   0.03207   0.02402  -0.0803   0.7851   0.3479
  -3.250  -0.1181   0.03193   0.02396  -0.0818   0.7810   0.3719
  -3.000  -0.1074   0.03241   0.02440  -0.0792   0.7714   0.3886
  -2.750  -0.0784   0.03245   0.02449  -0.0789   0.7648   0.4096
  -2.500  -0.0360   0.03214   0.02422  -0.0805   0.7614   0.4319
  -2.250  -0.0322   0.03276   0.02485  -0.0770   0.7501   0.4432
  -2.000   0.0038   0.03235   0.02443  -0.0777   0.7449   0.4591
  -1.750   0.0506   0.03162   0.02364  -0.0800   0.7421   0.4764
  -1.500   0.0523   0.03228   0.02427  -0.0763   0.7293   0.4858
  -1.250   0.0931   0.03162   0.02361  -0.0776   0.7253   0.5005
  -1.000   0.1416   0.03076   0.02270  -0.0800   0.7233   0.5171
  -0.750   0.1372   0.03172   0.02369  -0.0756   0.7093   0.5256
  -0.500   0.1812   0.03091   0.02287  -0.0773   0.7064   0.5412
  -0.250   0.2320   0.02993   0.02188  -0.0799   0.7047   0.5601
   0.000   0.2257   0.03095   0.02293  -0.0751   0.6902   0.5713
   0.250   0.2719   0.03003   0.02204  -0.0769   0.6879   0.5930
   0.500   0.3226   0.02910   0.02112  -0.0795   0.6861   0.6158
   0.750   0.3729   0.02817   0.02021  -0.0821   0.6844   0.6383
   1.000   0.3566   0.02946   0.02161  -0.0758   0.6694   0.6499
   1.250   0.4080   0.02845   0.02062  -0.0786   0.6675   0.6793
   1.500   0.4580   0.02731   0.01956  -0.0809   0.6657   0.7124
   1.750   0.4383   0.02870   0.02110  -0.0741   0.6510   0.7360
   2.000   0.4862   0.02764   0.02025  -0.0758   0.6489   0.7867
   2.250   0.5386   0.02665   0.01947  -0.0780   0.6471   0.8700
   2.500   0.5941   0.02784   0.02079  -0.0850   0.6351   0.9842
   2.750   0.6501   0.02712   0.01983  -0.0899   0.6316   1.0000
   3.000   0.7017   0.02638   0.01889  -0.0933   0.6289   1.0000
   3.250   0.6628   0.02875   0.02125  -0.0842   0.6156   1.0000
   3.500   0.7109   0.02811   0.02047  -0.0869   0.6124   1.0000
   3.750   0.7661   0.02731   0.01953  -0.0906   0.6098   1.0000
   4.000   0.7157   0.03028   0.02255  -0.0800   0.5962   1.0000
   4.250   0.7699   0.02946   0.02162  -0.0834   0.5934   1.0000
   4.500   0.8302   0.02843   0.02046  -0.0876   0.5909   1.0000
   4.750   0.7629   0.03214   0.02426  -0.0751   0.5769   1.0000
   5.000   0.8283   0.03076   0.02278  -0.0797   0.5746   1.0000
   5.250   0.8962   0.02944   0.02134  -0.0849   0.5722   1.0000
   5.500   0.8114   0.03405   0.02606  -0.0706   0.5578   1.0000
   5.750   0.8782   0.03240   0.02434  -0.0750   0.5559   1.0000
   6.000   0.9544   0.03082   0.02266  -0.0812   0.5537   1.0000
   6.250   0.8497   0.03678   0.02875  -0.0656   0.5385   1.0000
   6.500   0.9185   0.03469   0.02661  -0.0695   0.5372   1.0000
   6.750   1.0008   0.03264   0.02447  -0.0760   0.5354   1.0000
   7.000   0.8326   0.04399   0.03599  -0.0575   0.5134   1.0000
   7.250   0.9024   0.04084   0.03281  -0.0599   0.5140   1.0000
   7.500   0.9957   0.03697   0.02888  -0.0653   0.5148   1.0000
   7.750   0.9237   0.04321   0.03520  -0.0569   0.5003   1.0000
   8.000   0.9991   0.03994   0.03190  -0.0600   0.5000   1.0000
   8.250   1.0866   0.03689   0.02880  -0.0656   0.4990   1.0000
   8.500   0.9669   0.04620   0.03824  -0.0534   0.4817   1.0000
   8.750   1.0391   0.04294   0.03496  -0.0559   0.4813   1.0000
   9.000   1.1375   0.03890   0.03087  -0.0618   0.4807   1.0000
   9.250   1.0125   0.04906   0.04117  -0.0502   0.4630   1.0000
   9.500   1.0931   0.04493   0.03702  -0.0529   0.4630   1.0000
   9.750   1.1955   0.04066   0.03272  -0.0589   0.4623   1.0000
  10.000   1.0496   0.05289   0.04509  -0.0469   0.4438   1.0000
  10.250   1.1327   0.04820   0.04040  -0.0493   0.4437   1.0000
  11.250   1.1482   0.05379   0.04613  -0.0420   0.4091   1.0000
  11.500   1.3398   0.04100   0.03308  -0.0511   0.4055   1.0000
  11.750   0.8347   0.09869   0.09120  -0.0430   0.3573   1.0000
  12.000   0.8951   0.09348   0.08600  -0.0410   0.3552   1.0000
  12.250   0.9628   0.08680   0.07936  -0.0388   0.3544   1.0000
  12.500   1.0285   0.07993   0.07252  -0.0366   0.3542   1.0000
  12.750   1.1065   0.07174   0.06436  -0.0346   0.3548   1.0000
  13.000   1.2463   0.05791   0.05051  -0.0343   0.3569   1.0000
  13.250   1.3818   0.04814   0.04056  -0.0378   0.3523   1.0000
  13.500   1.2062   0.06646   0.05920  -0.0319   0.3388   1.0000
  13.750   1.4097   0.04895   0.04140  -0.0354   0.3362   1.0000
  14.000   1.1544   0.07780   0.07067  -0.0312   0.3183   1.0000
  14.250   1.2498   0.06795   0.06083  -0.0294   0.3168   1.0000
  14.500   1.2245   0.07322   0.06619  -0.0291   0.3062   1.0000
  14.750   1.3696   0.05876   0.05152  -0.0282   0.3011   1.0000
  15.000   1.3321   0.06460   0.05751  -0.0270   0.2909   1.0000
  15.250   1.3264   0.06733   0.06028  -0.0262   0.2804   1.0000
  15.500   1.3803   0.06326   0.05602  -0.0253   0.2685   1.0000
  15.750   1.3982   0.06337   0.05601  -0.0245   0.2556   1.0000
  16.000   1.3725   0.06848   0.06123  -0.0239   0.2438   1.0000
  16.250   1.3722   0.07092   0.06363  -0.0234   0.2317   1.0000
  16.500   1.3852   0.07191   0.06447  -0.0227   0.2200   1.0000
  16.750   1.3999   0.07277   0.06518  -0.0221   0.2094   1.0000
  17.000   1.3794   0.07801   0.07058  -0.0223   0.2014   1.0000
  17.250   1.4128   0.07679   0.06910  -0.0214   0.1930   1.0000
  17.500   1.3827   0.08338   0.07599  -0.0222   0.1874   1.0000
  17.750   1.3994   0.08423   0.07675  -0.0218   0.1815   1.0000
  18.000   1.4054   0.08658   0.07913  -0.0218   0.1768   1.0000
  18.250   1.3791   0.09315   0.08597  -0.0231   0.1731   1.0000
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