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E212 (10.55%) (e212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E212 (10.55%) (e212-il)
Reynolds number: 1,000,000
Max Cl/Cd: 119.78 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e212-il-1000000.txt
Download as CSV file: xf-e212-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E212  (10.55%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4035   0.08455   0.08306  -0.0362   1.0000   0.0159
 -10.250  -0.4106   0.08019   0.07873  -0.0366   1.0000   0.0162
 -10.000  -0.4298   0.07269   0.07125  -0.0382   1.0000   0.0162
  -9.500  -0.6769   0.03073   0.02783  -0.0833   0.9899   0.0101
  -9.250  -0.6569   0.02445   0.02086  -0.0883   0.9871   0.0097
  -9.000  -0.6269   0.02229   0.01844  -0.0909   0.9859   0.0098
  -8.750  -0.5956   0.02044   0.01636  -0.0932   0.9851   0.0099
  -8.500  -0.5677   0.01909   0.01486  -0.0942   0.9831   0.0102
  -8.250  -0.5410   0.01785   0.01346  -0.0948   0.9801   0.0103
  -8.000  -0.5105   0.01672   0.01220  -0.0961   0.9783   0.0105
  -7.750  -0.4784   0.01572   0.01109  -0.0976   0.9769   0.0106
  -7.500  -0.4454   0.01479   0.01006  -0.0992   0.9757   0.0108
  -7.250  -0.4115   0.01394   0.00912  -0.1010   0.9748   0.0110
  -7.000  -0.3769   0.01316   0.00826  -0.1028   0.9740   0.0111
  -6.750  -0.3416   0.01269   0.00774  -0.1046   0.9733   0.0114
  -6.500  -0.3167   0.01169   0.00664  -0.1045   0.9690   0.0117
  -6.250  -0.2851   0.01086   0.00573  -0.1056   0.9665   0.0123
  -6.000  -0.2515   0.01033   0.00515  -0.1071   0.9649   0.0130
  -5.750  -0.2168   0.00988   0.00466  -0.1086   0.9635   0.0137
  -5.500  -0.1814   0.00948   0.00422  -0.1103   0.9624   0.0144
  -5.250  -0.1456   0.00912   0.00382  -0.1121   0.9615   0.0151
  -5.000  -0.1093   0.00869   0.00335  -0.1139   0.9607   0.0173
  -4.750  -0.0843   0.00835   0.00302  -0.1132   0.9549   0.0222
  -4.500  -0.0511   0.00765   0.00259  -0.1147   0.9524   0.0747
  -4.250  -0.0160   0.00721   0.00231  -0.1165   0.9504   0.1149
  -4.000   0.0202   0.00684   0.00208  -0.1184   0.9485   0.1521
  -3.750   0.0520   0.00654   0.00189  -0.1193   0.9440   0.1864
  -3.500   0.0835   0.00629   0.00173  -0.1201   0.9383   0.2162
  -3.250   0.1205   0.00601   0.00156  -0.1222   0.9345   0.2547
  -3.000   0.1520   0.00580   0.00144  -0.1230   0.9268   0.2896
  -2.750   0.1873   0.00561   0.00132  -0.1246   0.9201   0.3235
  -2.500   0.2182   0.00546   0.00124  -0.1252   0.9098   0.3539
  -2.250   0.2497   0.00536   0.00116  -0.1259   0.8991   0.3790
  -2.000   0.2801   0.00529   0.00110  -0.1264   0.8868   0.4014
  -1.750   0.3094   0.00524   0.00105  -0.1266   0.8728   0.4235
  -1.500   0.3378   0.00522   0.00102  -0.1266   0.8578   0.4451
  -1.250   0.3656   0.00520   0.00100  -0.1265   0.8418   0.4671
  -1.000   0.3931   0.00521   0.00099  -0.1263   0.8251   0.4885
  -0.500   0.4473   0.00526   0.00101  -0.1257   0.7900   0.5298
  -0.250   0.4740   0.00531   0.00103  -0.1254   0.7718   0.5502
   0.000   0.5007   0.00536   0.00106  -0.1250   0.7530   0.5700
   0.250   0.5272   0.00542   0.00110  -0.1247   0.7331   0.5896
   0.500   0.5536   0.00550   0.00115  -0.1242   0.7127   0.6095
   0.750   0.5799   0.00559   0.00120  -0.1238   0.6918   0.6293
   1.000   0.6062   0.00568   0.00127  -0.1234   0.6699   0.6485
   1.250   0.6323   0.00579   0.00134  -0.1230   0.6480   0.6680
   1.500   0.6585   0.00590   0.00142  -0.1225   0.6250   0.6876
   1.750   0.6844   0.00603   0.00152  -0.1221   0.6020   0.7073
   2.000   0.7104   0.00616   0.00162  -0.1216   0.5780   0.7266
   2.250   0.7363   0.00631   0.00173  -0.1212   0.5543   0.7460
   2.500   0.7619   0.00648   0.00185  -0.1206   0.5291   0.7656
   2.750   0.7876   0.00664   0.00198  -0.1201   0.5031   0.7849
   3.000   0.8130   0.00682   0.00212  -0.1196   0.4777   0.8038
   3.250   0.8381   0.00701   0.00227  -0.1190   0.4528   0.8229
   3.500   0.8632   0.00721   0.00243  -0.1184   0.4275   0.8425
   3.750   0.8876   0.00741   0.00259  -0.1176   0.4021   0.8623
   4.000   0.9106   0.00769   0.00278  -0.1166   0.3680   0.8834
   4.250   0.9320   0.00801   0.00298  -0.1153   0.3289   0.9069
   4.500   0.9511   0.00823   0.00315  -0.1133   0.2992   0.9389
   4.750   0.9739   0.00851   0.00332  -0.1123   0.2664   1.0000
   5.000   0.9984   0.00895   0.00358  -0.1118   0.2317   1.0000
   5.250   1.0229   0.00938   0.00385  -0.1113   0.2000   1.0000
   5.500   1.0472   0.00982   0.00415  -0.1108   0.1700   1.0000
   5.750   1.0712   0.01028   0.00446  -0.1102   0.1423   1.0000
   6.000   1.0950   0.01075   0.00479  -0.1096   0.1173   1.0000
   6.250   1.1185   0.01124   0.00516  -0.1089   0.0935   1.0000
   6.500   1.1412   0.01180   0.00557  -0.1081   0.0690   1.0000
   6.750   1.1631   0.01243   0.00604  -0.1071   0.0451   1.0000
   7.000   1.1827   0.01329   0.00670  -0.1058   0.0177   1.0000
   7.250   1.2050   0.01387   0.00725  -0.1048   0.0122   1.0000
   7.500   1.2283   0.01432   0.00772  -0.1040   0.0110   1.0000
   7.750   1.2507   0.01484   0.00827  -0.1031   0.0101   1.0000
   8.000   1.2719   0.01549   0.00898  -0.1019   0.0094   1.0000
   8.250   1.2942   0.01597   0.00951  -0.1010   0.0091   1.0000
   8.500   1.3158   0.01651   0.01011  -0.1000   0.0089   1.0000
   8.750   1.3365   0.01710   0.01076  -0.0988   0.0085   1.0000
   9.000   1.3564   0.01774   0.01145  -0.0975   0.0083   1.0000
   9.250   1.3754   0.01842   0.01219  -0.0960   0.0080   1.0000
   9.500   1.3932   0.01915   0.01297  -0.0945   0.0077   1.0000
   9.750   1.4092   0.01999   0.01388  -0.0926   0.0074   1.0000
  10.000   1.4187   0.02111   0.01509  -0.0896   0.0071   1.0000
  10.250   1.4219   0.02253   0.01663  -0.0857   0.0069   1.0000
  10.500   1.4290   0.02371   0.01790  -0.0825   0.0069   1.0000
  10.750   1.4405   0.02459   0.01886  -0.0801   0.0068   1.0000
  11.000   1.4502   0.02561   0.01996  -0.0776   0.0067   1.0000
  11.250   1.4589   0.02671   0.02115  -0.0750   0.0067   1.0000
  11.500   1.4662   0.02797   0.02250  -0.0724   0.0066   1.0000
  11.750   1.4725   0.02933   0.02396  -0.0699   0.0066   1.0000
  12.000   1.4776   0.03084   0.02558  -0.0674   0.0065   1.0000
  12.250   1.4821   0.03247   0.02731  -0.0651   0.0064   1.0000
  12.500   1.4859   0.03422   0.02916  -0.0630   0.0064   1.0000
  12.750   1.4883   0.03618   0.03124  -0.0610   0.0063   1.0000
  13.000   1.4895   0.03834   0.03352  -0.0592   0.0063   1.0000
  13.250   1.4900   0.04069   0.03599  -0.0576   0.0062   1.0000
  13.500   1.4897   0.04323   0.03865  -0.0563   0.0062   1.0000
  13.750   1.4879   0.04607   0.04162  -0.0553   0.0061   1.0000
  14.000   1.4850   0.04918   0.04486  -0.0546   0.0061   1.0000
  14.250   1.4817   0.05248   0.04829  -0.0543   0.0060   1.0000
  14.500   1.4762   0.05627   0.05222  -0.0543   0.0060   1.0000
  14.750   1.4703   0.06030   0.05640  -0.0548   0.0059   1.0000
  15.000   1.4627   0.06478   0.06103  -0.0557   0.0059   1.0000
  15.250   1.4543   0.06965   0.06604  -0.0571   0.0059   1.0000
  15.500   1.4445   0.07502   0.07156  -0.0589   0.0058   1.0000
  15.750   1.4338   0.08079   0.07748  -0.0613   0.0058   1.0000
  16.000   1.4213   0.08715   0.08400  -0.0642   0.0058   1.0000
  16.250   1.4085   0.09390   0.09089  -0.0675   0.0058   1.0000
  16.500   1.3942   0.10119   0.09834  -0.0714   0.0058   1.0000
  16.750   1.3784   0.10907   0.10639  -0.0758   0.0058   1.0000
  17.000   1.3618   0.11746   0.11493  -0.0807   0.0058   1.0000
  17.250   1.3438   0.12647   0.12410  -0.0862   0.0058   1.0000
  17.500   1.3277   0.13530   0.13308  -0.0918   0.0058   1.0000
  17.750   1.3084   0.14524   0.14319  -0.0982   0.0059   1.0000
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