Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

E212 (10.55%) (e212-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E212 (10.55%) (e212-il)
Reynolds number: 500,000
Max Cl/Cd: 108.43 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e212-il-500000.txt
Download as CSV file: xf-e212-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4612   0.08966   0.08743  -0.0359   1.0000   0.0281
  -9.250  -0.4687   0.08544   0.08325  -0.0369   1.0000   0.0289
  -8.250  -0.6134   0.03452   0.03099  -0.0724   0.9930   0.0188
  -8.000  -0.5936   0.02467   0.01995  -0.0776   0.9895   0.0157
  -7.750  -0.5619   0.02246   0.01742  -0.0798   0.9876   0.0156
  -7.500  -0.5287   0.02068   0.01540  -0.0818   0.9862   0.0157
  -7.250  -0.4946   0.01913   0.01369  -0.0839   0.9850   0.0159
  -7.000  -0.4643   0.01799   0.01246  -0.0850   0.9822   0.0163
  -6.750  -0.4327   0.01705   0.01143  -0.0863   0.9794   0.0169
  -6.500  -0.3987   0.01601   0.01028  -0.0880   0.9772   0.0172
  -6.250  -0.3632   0.01507   0.00925  -0.0899   0.9755   0.0177
  -6.000  -0.3265   0.01428   0.00837  -0.0921   0.9741   0.0183
  -5.750  -0.2890   0.01360   0.00761  -0.0944   0.9730   0.0190
  -5.500  -0.2607   0.01292   0.00686  -0.0947   0.9682   0.0198
  -5.250  -0.2258   0.01223   0.00610  -0.0964   0.9655   0.0217
  -5.000  -0.1894   0.01179   0.00561  -0.0983   0.9635   0.0243
  -4.750  -0.1517   0.01117   0.00503  -0.1005   0.9619   0.0363
  -4.500  -0.1135   0.01034   0.00454  -0.1032   0.9608   0.1056
  -4.250  -0.0849   0.00993   0.00426  -0.1035   0.9554   0.1426
  -4.000  -0.0500   0.00953   0.00401  -0.1052   0.9523   0.1849
  -3.750  -0.0129   0.00914   0.00377  -0.1072   0.9502   0.2286
  -3.500   0.0253   0.00879   0.00354  -0.1095   0.9486   0.2687
  -3.250   0.0642   0.00844   0.00333  -0.1119   0.9473   0.3141
  -3.000   0.0916   0.00820   0.00317  -0.1117   0.9403   0.3449
  -2.750   0.1284   0.00790   0.00295  -0.1136   0.9375   0.3782
  -2.500   0.1674   0.00763   0.00275  -0.1158   0.9353   0.4098
  -2.250   0.2024   0.00740   0.00259  -0.1172   0.9308   0.4371
  -2.000   0.2352   0.00721   0.00244  -0.1181   0.9243   0.4625
  -1.750   0.2736   0.00699   0.00227  -0.1202   0.9200   0.4896
  -1.500   0.3046   0.00684   0.00218  -0.1207   0.9109   0.5137
  -1.250   0.3417   0.00668   0.00205  -0.1225   0.9039   0.5391
  -1.000   0.3731   0.00657   0.00199  -0.1231   0.8925   0.5623
  -0.750   0.4044   0.00650   0.00193  -0.1236   0.8802   0.5855
  -0.500   0.4351   0.00643   0.00189  -0.1240   0.8668   0.6073
  -0.250   0.4648   0.00641   0.00187  -0.1242   0.8523   0.6292
   0.000   0.4936   0.00640   0.00187  -0.1242   0.8366   0.6502
   0.250   0.5217   0.00642   0.00189  -0.1240   0.8201   0.6710
   0.500   0.5492   0.00646   0.00191  -0.1237   0.8027   0.6920
   0.750   0.5760   0.00651   0.00195  -0.1233   0.7846   0.7122
   1.000   0.6022   0.00657   0.00201  -0.1227   0.7651   0.7327
   1.250   0.6281   0.00665   0.00208  -0.1221   0.7448   0.7532
   1.500   0.6534   0.00675   0.00215  -0.1213   0.7242   0.7729
   1.750   0.6783   0.00685   0.00225  -0.1205   0.7024   0.7930
   2.000   0.7027   0.00699   0.00234  -0.1196   0.6803   0.8134
   2.250   0.7267   0.00710   0.00244  -0.1185   0.6573   0.8332
   2.500   0.7497   0.00725   0.00255  -0.1173   0.6343   0.8536
   2.750   0.7724   0.00738   0.00267  -0.1160   0.6101   0.8753
   3.000   0.7929   0.00751   0.00277  -0.1142   0.5862   0.8986
   3.250   0.8113   0.00763   0.00285  -0.1119   0.5616   0.9274
   3.500   0.8338   0.00769   0.00288  -0.1106   0.5361   1.0000
   3.750   0.8602   0.00796   0.00305  -0.1104   0.5091   1.0000
   4.000   0.8861   0.00825   0.00322  -0.1101   0.4821   1.0000
   4.250   0.9115   0.00856   0.00342  -0.1097   0.4541   1.0000
   4.500   0.9367   0.00889   0.00364  -0.1093   0.4243   1.0000
   4.750   0.9610   0.00927   0.00387  -0.1087   0.3891   1.0000
   5.000   0.9849   0.00969   0.00413  -0.1080   0.3524   1.0000
   5.250   1.0084   0.01016   0.00442  -0.1073   0.3142   1.0000
   5.500   1.0319   0.01064   0.00475  -0.1067   0.2788   1.0000
   5.750   1.0550   0.01115   0.00509  -0.1060   0.2445   1.0000
   6.000   1.0776   0.01172   0.00547  -0.1052   0.2056   1.0000
   6.250   1.0999   0.01231   0.00589  -0.1043   0.1726   1.0000
   6.500   1.1223   0.01289   0.00632  -0.1035   0.1433   1.0000
   6.750   1.1442   0.01350   0.00679  -0.1026   0.1154   1.0000
   7.000   1.1659   0.01413   0.00728  -0.1017   0.0913   1.0000
   7.250   1.1869   0.01481   0.00783  -0.1007   0.0676   1.0000
   7.500   1.2043   0.01584   0.00862  -0.0991   0.0344   1.0000
   7.750   1.2224   0.01680   0.00949  -0.0975   0.0198   1.0000
   8.000   1.2419   0.01760   0.01030  -0.0961   0.0166   1.0000
   8.250   1.2622   0.01826   0.01102  -0.0948   0.0154   1.0000
   8.500   1.2817   0.01896   0.01179  -0.0934   0.0145   1.0000
   8.750   1.2999   0.01974   0.01265  -0.0919   0.0137   1.0000
   9.000   1.3153   0.02070   0.01367  -0.0899   0.0131   1.0000
   9.250   1.3252   0.02193   0.01500  -0.0870   0.0126   1.0000
   9.500   1.3363   0.02295   0.01612  -0.0844   0.0124   1.0000
   9.750   1.3477   0.02394   0.01720  -0.0818   0.0122   1.0000
  10.000   1.3579   0.02502   0.01838  -0.0792   0.0119   1.0000
  10.250   1.3670   0.02622   0.01968  -0.0765   0.0117   1.0000
  10.500   1.3753   0.02751   0.02107  -0.0738   0.0115   1.0000
  10.750   1.3834   0.02884   0.02251  -0.0713   0.0113   1.0000
  11.000   1.3913   0.03024   0.02401  -0.0689   0.0110   1.0000
  11.250   1.3988   0.03169   0.02555  -0.0667   0.0108   1.0000
  11.500   1.4054   0.03327   0.02723  -0.0645   0.0105   1.0000
  11.750   1.4110   0.03501   0.02908  -0.0624   0.0104   1.0000
  12.000   1.4157   0.03695   0.03114  -0.0605   0.0103   1.0000
  12.250   1.4197   0.03904   0.03334  -0.0586   0.0102   1.0000
  12.500   1.4228   0.04130   0.03574  -0.0570   0.0100   1.0000
  12.750   1.4250   0.04377   0.03834  -0.0555   0.0100   1.0000
  13.000   1.4261   0.04645   0.04116  -0.0541   0.0099   1.0000
  13.250   1.4257   0.04940   0.04427  -0.0530   0.0098   1.0000
  13.500   1.4239   0.05260   0.04763  -0.0521   0.0098   1.0000
  13.750   1.4201   0.05612   0.05133  -0.0516   0.0098   1.0000
  14.000   1.4146   0.05998   0.05536  -0.0513   0.0097   1.0000
  14.250   1.4071   0.06421   0.05978  -0.0516   0.0097   1.0000
  14.500   1.3981   0.06878   0.06455  -0.0523   0.0097   1.0000
  14.750   1.3873   0.07385   0.06980  -0.0535   0.0097   1.0000
  15.000   1.3751   0.07937   0.07552  -0.0554   0.0097   1.0000
  15.250   1.3615   0.08545   0.08181  -0.0580   0.0098   1.0000
  15.500   1.3466   0.09212   0.08868  -0.0612   0.0098   1.0000
  15.750   1.3294   0.09962   0.09640  -0.0653   0.0099   1.0000
  16.000   1.3093   0.10827   0.10528  -0.0703   0.0100   1.0000
  16.250   1.2853   0.11836   0.11562  -0.0766   0.0101   1.0000
  16.500   1.2442   0.13366   0.13128  -0.0871   0.0105   1.0000
  16.750   1.1954   0.15293   0.15088  -0.1004   0.0109   1.0000
  17.000   1.1048   0.19025   0.18844  -0.1238   0.0123   1.0000
<< Back to E212 (10.55%) (e212-il)

Polar data table (+)

Polar graphs


<< Back to E212 (10.55%) (e212-il)