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E212 (10.55%) (e212-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E212 (10.55%) (e212-il)
Reynolds number: 500,000
Max Cl/Cd: 91.75 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e212-il-500000-n5.txt
Download as CSV file: xf-e212-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.5991   0.08555   0.08299  -0.0415   1.0000   0.0077
 -11.750  -0.6371   0.07409   0.07146  -0.0474   1.0000   0.0076
 -11.500  -0.6689   0.06425   0.06150  -0.0531   1.0000   0.0076
 -11.250  -0.6930   0.05665   0.05379  -0.0577   1.0000   0.0076
 -11.000  -0.7163   0.05001   0.04703  -0.0617   1.0000   0.0076
 -10.750  -0.7389   0.04504   0.04198  -0.0638   1.0000   0.0075
 -10.500  -0.7610   0.04090   0.03772  -0.0657   0.9992   0.0075
 -10.250  -0.7426   0.03505   0.03145  -0.0765   0.9949   0.0076
 -10.000  -0.7247   0.03168   0.02775  -0.0804   0.9916   0.0076
  -9.750  -0.7017   0.02915   0.02491  -0.0834   0.9887   0.0077
  -9.500  -0.6756   0.02698   0.02246  -0.0860   0.9867   0.0078
  -9.250  -0.6479   0.02480   0.02001  -0.0886   0.9851   0.0079
  -9.000  -0.6255   0.02269   0.01767  -0.0897   0.9821   0.0081
  -8.750  -0.5997   0.02119   0.01602  -0.0908   0.9793   0.0083
  -8.500  -0.5709   0.02007   0.01481  -0.0922   0.9772   0.0086
  -8.250  -0.5404   0.01905   0.01367  -0.0937   0.9755   0.0089
  -8.000  -0.5090   0.01800   0.01250  -0.0953   0.9742   0.0091
  -7.750  -0.4786   0.01704   0.01141  -0.0965   0.9725   0.0092
  -7.500  -0.4541   0.01620   0.01048  -0.0964   0.9681   0.0095
  -7.250  -0.4239   0.01540   0.00959  -0.0974   0.9656   0.0097
  -7.000  -0.3920   0.01466   0.00876  -0.0988   0.9637   0.0100
  -6.750  -0.3590   0.01399   0.00799  -0.1003   0.9622   0.0103
  -6.500  -0.3251   0.01338   0.00731  -0.1019   0.9609   0.0106
  -6.250  -0.3010   0.01287   0.00674  -0.1013   0.9551   0.0109
  -6.000  -0.2693   0.01220   0.00600  -0.1025   0.9523   0.0114
  -5.750  -0.2361   0.01168   0.00542  -0.1038   0.9502   0.0120
  -5.500  -0.2023   0.01126   0.00495  -0.1052   0.9485   0.0131
  -5.250  -0.1754   0.01092   0.00456  -0.1051   0.9431   0.0140
  -5.000  -0.1445   0.01055   0.00413  -0.1058   0.9393   0.0152
  -4.750  -0.1108   0.01016   0.00373  -0.1071   0.9366   0.0180
  -4.500  -0.0749   0.00964   0.00332  -0.1090   0.9345   0.0396
  -4.250  -0.0461   0.00923   0.00302  -0.1094   0.9280   0.0697
  -4.000  -0.0110   0.00880   0.00275  -0.1112   0.9239   0.1058
  -3.750   0.0268   0.00841   0.00250  -0.1135   0.9205   0.1459
  -3.500   0.0589   0.00813   0.00231  -0.1145   0.9135   0.1781
  -3.250   0.0951   0.00785   0.00212  -0.1164   0.9074   0.2139
  -3.000   0.1290   0.00758   0.00197  -0.1178   0.8992   0.2575
  -2.750   0.1648   0.00735   0.00182  -0.1196   0.8906   0.2948
  -2.500   0.1968   0.00722   0.00171  -0.1204   0.8790   0.3196
  -2.250   0.2285   0.00711   0.00162  -0.1212   0.8668   0.3418
  -2.000   0.2593   0.00703   0.00154  -0.1217   0.8534   0.3651
  -1.750   0.2892   0.00697   0.00148  -0.1221   0.8390   0.3873
  -1.500   0.3182   0.00693   0.00143  -0.1222   0.8234   0.4102
  -1.250   0.3465   0.00692   0.00140  -0.1223   0.8067   0.4316
  -1.000   0.3743   0.00692   0.00139  -0.1221   0.7891   0.4528
  -0.750   0.4017   0.00695   0.00138  -0.1219   0.7708   0.4733
  -0.500   0.4287   0.00698   0.00139  -0.1216   0.7520   0.4933
  -0.250   0.4555   0.00703   0.00142  -0.1213   0.7324   0.5131
   0.000   0.4820   0.00710   0.00145  -0.1209   0.7126   0.5327
   0.250   0.5084   0.00718   0.00149  -0.1205   0.6929   0.5522
   0.500   0.5348   0.00725   0.00155  -0.1201   0.6728   0.5717
   0.750   0.5609   0.00735   0.00162  -0.1197   0.6519   0.5913
   1.000   0.5870   0.00745   0.00170  -0.1192   0.6310   0.6112
   1.500   0.6386   0.00770   0.00189  -0.1183   0.5862   0.6504
   1.750   0.6643   0.00784   0.00200  -0.1178   0.5633   0.6699
   2.000   0.6898   0.00800   0.00212  -0.1172   0.5401   0.6895
   2.250   0.7153   0.00816   0.00226  -0.1167   0.5163   0.7088
   2.750   0.7656   0.00853   0.00257  -0.1155   0.4680   0.7473
   3.000   0.7905   0.00873   0.00273  -0.1149   0.4426   0.7669
   3.250   0.8151   0.00896   0.00291  -0.1142   0.4172   0.7863
   3.500   0.8392   0.00920   0.00312  -0.1134   0.3912   0.8060
   3.750   0.8632   0.00943   0.00332  -0.1126   0.3659   0.8266
   4.000   0.8866   0.00967   0.00353  -0.1116   0.3418   0.8475
   4.250   0.9092   0.00991   0.00375  -0.1105   0.3187   0.8700
   4.500   0.9296   0.01022   0.00398  -0.1089   0.2875   0.8956
   4.750   0.9468   0.01057   0.00421  -0.1067   0.2492   0.9308
   5.000   0.9692   0.01102   0.00447  -0.1058   0.2082   1.0000
   5.250   0.9931   0.01151   0.00481  -0.1052   0.1760   1.0000
   5.500   1.0172   0.01197   0.00515  -0.1047   0.1512   1.0000
   6.000   1.0638   0.01302   0.00593  -0.1034   0.1000   1.0000
   6.250   1.0864   0.01359   0.00637  -0.1026   0.0763   1.0000
   6.500   1.1095   0.01410   0.00680  -0.1019   0.0599   1.0000
   6.750   1.1314   0.01472   0.00730  -0.1010   0.0419   1.0000
   7.000   1.1532   0.01534   0.00784  -0.1001   0.0274   1.0000
   7.250   1.1737   0.01606   0.00848  -0.0989   0.0141   1.0000
   7.500   1.1956   0.01663   0.00906  -0.0980   0.0113   1.0000
   7.750   1.2172   0.01720   0.00966  -0.0970   0.0099   1.0000
   8.000   1.2386   0.01778   0.01028  -0.0959   0.0091   1.0000
   8.250   1.2599   0.01833   0.01090  -0.0949   0.0086   1.0000
   8.500   1.2804   0.01891   0.01156  -0.0937   0.0082   1.0000
   8.750   1.3002   0.01955   0.01226  -0.0925   0.0079   1.0000
   9.000   1.3189   0.02024   0.01302  -0.0911   0.0075   1.0000
   9.250   1.3364   0.02099   0.01384  -0.0895   0.0073   1.0000
   9.500   1.3511   0.02182   0.01474  -0.0874   0.0071   1.0000
   9.750   1.3628   0.02280   0.01582  -0.0849   0.0068   1.0000
  10.000   1.3737   0.02380   0.01691  -0.0824   0.0067   1.0000
  10.250   1.3858   0.02470   0.01789  -0.0801   0.0066   1.0000
  10.500   1.3966   0.02568   0.01897  -0.0777   0.0065   1.0000
  10.750   1.4065   0.02675   0.02013  -0.0753   0.0064   1.0000
  11.000   1.4150   0.02792   0.02140  -0.0728   0.0063   1.0000
  11.250   1.4226   0.02918   0.02277  -0.0704   0.0062   1.0000
  11.500   1.4292   0.03055   0.02426  -0.0681   0.0061   1.0000
  11.750   1.4352   0.03201   0.02584  -0.0658   0.0059   1.0000
  12.000   1.4402   0.03362   0.02755  -0.0637   0.0058   1.0000
  12.250   1.4445   0.03533   0.02937  -0.0618   0.0057   1.0000
  12.500   1.4475   0.03726   0.03142  -0.0600   0.0056   1.0000
  12.750   1.4499   0.03932   0.03360  -0.0584   0.0055   1.0000
  13.000   1.4511   0.04162   0.03602  -0.0571   0.0054   1.0000
  13.250   1.4509   0.04418   0.03870  -0.0560   0.0053   1.0000
  13.500   1.4497   0.04699   0.04164  -0.0552   0.0053   1.0000
  13.750   1.4475   0.05010   0.04488  -0.0548   0.0052   1.0000
  14.000   1.4444   0.05346   0.04837  -0.0547   0.0052   1.0000
  14.250   1.4398   0.05720   0.05227  -0.0549   0.0051   1.0000
  14.500   1.4347   0.06122   0.05643  -0.0556   0.0051   1.0000
  14.750   1.4282   0.06566   0.06101  -0.0566   0.0051   1.0000
  15.000   1.4209   0.07045   0.06594  -0.0581   0.0050   1.0000
  15.250   1.4128   0.07562   0.07126  -0.0600   0.0050   1.0000
  15.500   1.4037   0.08117   0.07696  -0.0622   0.0050   1.0000
  15.750   1.3935   0.08713   0.08307  -0.0649   0.0050   1.0000
  16.000   1.3829   0.09342   0.08950  -0.0679   0.0049   1.0000
  16.250   1.3717   0.10005   0.09628  -0.0713   0.0049   1.0000
  16.500   1.3599   0.10696   0.10334  -0.0749   0.0049   1.0000
  16.750   1.3479   0.11415   0.11068  -0.0789   0.0049   1.0000
  17.000   1.3358   0.12154   0.11822  -0.0831   0.0049   1.0000
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