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GOE 400 AIRFOIL (goe400-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 400 AIRFOIL (goe400-il)
Reynolds number: 1,000,000
Max Cl/Cd: 101.4 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe400-il-1000000-n5.txt
Download as CSV file: xf-goe400-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 400 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4986   0.13165   0.13004   0.0168   1.0000   0.0053
 -11.000  -0.5007   0.12560   0.12400   0.0146   1.0000   0.0058
 -10.750  -0.4995   0.12083   0.11923   0.0127   1.0000   0.0061
 -10.500  -0.4924   0.11786   0.11627   0.0113   1.0000   0.0063
 -10.250  -0.4853   0.11485   0.11325   0.0099   1.0000   0.0064
  -7.750  -0.4270   0.01843   0.01530  -0.0828   0.9105   0.0182
  -7.500  -0.4030   0.01740   0.01401  -0.0824   0.8769   0.0190
  -7.250  -0.3782   0.01661   0.01297  -0.0821   0.8418   0.0195
  -7.000  -0.3524   0.01600   0.01211  -0.0818   0.8084   0.0198
  -6.750  -0.3259   0.01568   0.01159  -0.0816   0.7802   0.0201
  -6.500  -0.2999   0.01439   0.00999  -0.0818   0.7581   0.0207
  -6.250  -0.2730   0.01394   0.00939  -0.0817   0.7395   0.0213
  -5.750  -0.2182   0.01367   0.00897  -0.0814   0.7106   0.0223
  -5.500  -0.1906   0.01341   0.00862  -0.0813   0.6988   0.0228
  -5.250  -0.1632   0.01295   0.00801  -0.0812   0.6879   0.0233
  -5.000  -0.1357   0.01249   0.00741  -0.0811   0.6776   0.0238
  -4.750  -0.1080   0.01206   0.00685  -0.0811   0.6677   0.0244
  -4.500  -0.0803   0.01154   0.00617  -0.0810   0.6589   0.0247
  -4.250  -0.0526   0.01108   0.00556  -0.0809   0.6496   0.0250
  -4.000  -0.0248   0.01064   0.00500  -0.0808   0.6411   0.0252
  -3.750   0.0030   0.01027   0.00450  -0.0807   0.6324   0.0255
  -3.500   0.0309   0.00992   0.00404  -0.0806   0.6239   0.0257
  -3.250   0.0588   0.00961   0.00363  -0.0804   0.6157   0.0259
  -3.000   0.0868   0.00934   0.00326  -0.0803   0.6071   0.0261
  -2.750   0.1148   0.00914   0.00299  -0.0802   0.5993   0.0264
  -2.500   0.1428   0.00897   0.00276  -0.0800   0.5912   0.0266
  -2.250   0.1708   0.00878   0.00251  -0.0799   0.5838   0.0268
  -2.000   0.1988   0.00862   0.00229  -0.0797   0.5758   0.0270
  -1.750   0.2269   0.00847   0.00208  -0.0796   0.5684   0.0271
  -1.500   0.2549   0.00818   0.00170  -0.0795   0.5604   0.0283
  -1.250   0.2829   0.00803   0.00151  -0.0793   0.5529   0.0293
  -1.000   0.3110   0.00794   0.00136  -0.0792   0.5446   0.0302
  -0.750   0.3390   0.00786   0.00126  -0.0791   0.5370   0.0310
  -0.500   0.3671   0.00781   0.00117  -0.0789   0.5283   0.0317
  -0.250   0.3951   0.00777   0.00110  -0.0788   0.5191   0.0325
   0.000   0.4230   0.00776   0.00104  -0.0787   0.5063   0.0333
   0.250   0.4509   0.00777   0.00100  -0.0785   0.4921   0.0343
   0.500   0.4787   0.00778   0.00097  -0.0784   0.4786   0.0356
   1.000   0.5342   0.00776   0.00099  -0.0782   0.4511   0.0791
   1.250   0.5620   0.00784   0.00106  -0.0780   0.4389   0.0881
   1.500   0.5897   0.00794   0.00111  -0.0779   0.4235   0.0920
   1.750   0.6173   0.00808   0.00118  -0.0778   0.4051   0.0941
   2.000   0.6448   0.00818   0.00123  -0.0776   0.3868   0.0964
   2.250   0.6723   0.00827   0.00128  -0.0775   0.3725   0.0983
   2.500   0.6999   0.00836   0.00135  -0.0774   0.3600   0.1000
   2.750   0.7274   0.00846   0.00142  -0.0772   0.3474   0.1015
   3.000   0.7549   0.00858   0.00151  -0.0771   0.3347   0.1039
   3.250   0.7823   0.00871   0.00162  -0.0770   0.3214   0.1062
   3.500   0.8095   0.00885   0.00172  -0.0769   0.3069   0.1068
   3.750   0.8367   0.00900   0.00183  -0.0767   0.2922   0.1072
   4.000   0.8639   0.00914   0.00195  -0.0766   0.2783   0.1081
   4.250   0.8910   0.00930   0.00207  -0.0764   0.2640   0.1095
   4.500   0.9176   0.00953   0.00224  -0.0762   0.2432   0.1110
   4.750   0.9443   0.00975   0.00241  -0.0761   0.2248   0.1127
   5.000   0.9704   0.01009   0.00265  -0.0758   0.1973   0.1145
   5.250   0.9952   0.01065   0.00301  -0.0755   0.1526   0.1166
   5.500   1.0188   0.01142   0.00348  -0.0751   0.0957   0.1191
   6.000   1.0712   0.01191   0.00402  -0.0747   0.0817   0.1520
   6.500   1.1215   0.01106   0.00470  -0.0741   0.0723   1.0000
   6.750   1.1472   0.01139   0.00500  -0.0738   0.0654   1.0000
   7.000   1.1714   0.01196   0.00540  -0.0734   0.0400   1.0000
   7.250   1.1946   0.01269   0.00601  -0.0729   0.0186   1.0000
   7.500   1.2193   0.01312   0.00643  -0.0725   0.0145   1.0000
   7.750   1.2444   0.01349   0.00682  -0.0721   0.0126   1.0000
   8.000   1.2689   0.01391   0.00726  -0.0717   0.0110   1.0000
   8.250   1.2930   0.01440   0.00777  -0.0712   0.0095   1.0000
   8.500   1.3174   0.01480   0.00820  -0.0708   0.0090   1.0000
   8.750   1.3415   0.01523   0.00867  -0.0704   0.0084   1.0000
   9.000   1.3650   0.01571   0.00917  -0.0699   0.0077   1.0000
   9.250   1.3879   0.01626   0.00977  -0.0693   0.0071   1.0000
   9.500   1.4103   0.01685   0.01040  -0.0686   0.0065   1.0000
   9.750   1.4330   0.01735   0.01094  -0.0681   0.0062   1.0000
  10.000   1.4551   0.01790   0.01154  -0.0674   0.0059   1.0000
  10.250   1.4767   0.01849   0.01218  -0.0667   0.0056   1.0000
  10.500   1.4976   0.01912   0.01285  -0.0660   0.0053   1.0000
  10.750   1.5175   0.01982   0.01361  -0.0651   0.0050   1.0000
  11.000   1.5357   0.02067   0.01453  -0.0640   0.0047   1.0000
  11.250   1.5529   0.02156   0.01549  -0.0629   0.0045   1.0000
  11.500   1.5705   0.02233   0.01634  -0.0618   0.0044   1.0000
  11.750   1.5865   0.02319   0.01727  -0.0605   0.0043   1.0000
  12.000   1.6011   0.02411   0.01827  -0.0591   0.0042   1.0000
  12.250   1.6130   0.02506   0.01930  -0.0573   0.0040   1.0000
  12.500   1.6218   0.02610   0.02043  -0.0553   0.0039   1.0000
  12.750   1.6295   0.02727   0.02169  -0.0534   0.0038   1.0000
  13.000   1.6364   0.02861   0.02311  -0.0518   0.0036   1.0000
  13.250   1.6427   0.03015   0.02473  -0.0505   0.0035   1.0000
  13.500   1.6477   0.03196   0.02663  -0.0496   0.0034   1.0000
  13.750   1.6516   0.03407   0.02883  -0.0489   0.0034   1.0000
  14.000   1.6534   0.03656   0.03142  -0.0486   0.0033   1.0000
  14.250   1.6533   0.03944   0.03440  -0.0486   0.0032   1.0000
  14.500   1.6503   0.04278   0.03786  -0.0488   0.0031   1.0000
  14.750   1.6437   0.04667   0.04188  -0.0493   0.0031   1.0000
  15.000   1.6353   0.05089   0.04622  -0.0499   0.0030   1.0000
  15.250   1.6271   0.05515   0.05061  -0.0507   0.0030   1.0000
  15.500   1.6193   0.05941   0.05499  -0.0515   0.0030   1.0000
  15.750   1.6100   0.06397   0.05968  -0.0526   0.0030   1.0000
  16.000   1.5988   0.06889   0.06471  -0.0538   0.0029   1.0000
  16.250   1.5872   0.07408   0.07003  -0.0553   0.0029   1.0000
  16.500   1.5747   0.07960   0.07568  -0.0570   0.0029   1.0000
  16.750   1.5612   0.08541   0.08162  -0.0590   0.0029   1.0000
  17.000   1.5466   0.09158   0.08791  -0.0612   0.0029   1.0000
  17.250   1.5317   0.09792   0.09437  -0.0635   0.0029   1.0000
  17.500   1.5163   0.10443   0.10100  -0.0660   0.0029   1.0000
  17.750   1.5001   0.11125   0.10794  -0.0688   0.0029   1.0000
  18.000   1.4844   0.11810   0.11490  -0.0717   0.0029   1.0000
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