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E210 (13.64%) (e210-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E210 (13.64%) (e210-il)
Reynolds number: 500,000
Max Cl/Cd: 112.97 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e210-il-500000.txt
Download as CSV file: xf-e210-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E210  (13.64%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3615   0.10405   0.10189  -0.0392   1.0000   0.0244
 -10.000  -0.3632   0.10130   0.09917  -0.0390   1.0000   0.0249
  -9.250  -0.5023   0.04090   0.03799  -0.0951   0.9785   0.0175
  -9.000  -0.4908   0.03399   0.03051  -0.1020   0.9729   0.0173
  -8.750  -0.4760   0.02999   0.02604  -0.1039   0.9659   0.0176
  -8.500  -0.4495   0.02703   0.02266  -0.1063   0.9619   0.0178
  -8.250  -0.4202   0.02362   0.01878  -0.1092   0.9596   0.0185
  -8.000  -0.3978   0.02204   0.01715  -0.1093   0.9532   0.0193
  -7.750  -0.3662   0.02092   0.01593  -0.1107   0.9494   0.0202
  -7.500  -0.3317   0.01948   0.01431  -0.1127   0.9470   0.0209
  -7.250  -0.3019   0.01818   0.01285  -0.1135   0.9425   0.0216
  -7.000  -0.2736   0.01719   0.01172  -0.1138   0.9363   0.0223
  -6.750  -0.2386   0.01630   0.01069  -0.1153   0.9333   0.0229
  -6.500  -0.2147   0.01470   0.00904  -0.1151   0.9255   0.0242
  -6.250  -0.1814   0.01388   0.00819  -0.1164   0.9200   0.0255
  -6.000  -0.1485   0.01314   0.00739  -0.1175   0.9126   0.0265
  -5.750  -0.1093   0.01242   0.00659  -0.1200   0.9058   0.0278
  -5.500  -0.0715   0.01171   0.00580  -0.1223   0.8960   0.0293
  -5.250  -0.0318   0.01098   0.00500  -0.1250   0.8846   0.0319
  -5.000   0.0055   0.01054   0.00446  -0.1270   0.8688   0.0344
  -4.750   0.0387   0.01012   0.00392  -0.1282   0.8496   0.0383
  -4.500   0.0690   0.00981   0.00352  -0.1287   0.8294   0.0473
  -4.250   0.0957   0.00933   0.00315  -0.1287   0.8087   0.0900
  -4.000   0.1219   0.00906   0.00292  -0.1285   0.7885   0.1315
  -3.750   0.1478   0.00884   0.00274  -0.1282   0.7695   0.1738
  -3.250   0.1989   0.00833   0.00244  -0.1277   0.7354   0.2936
  -3.000   0.2243   0.00808   0.00237  -0.1274   0.7199   0.3750
  -2.750   0.2505   0.00804   0.00237  -0.1271   0.7056   0.4291
  -2.500   0.2770   0.00806   0.00237  -0.1268   0.6922   0.4625
  -2.250   0.3036   0.00810   0.00238  -0.1264   0.6796   0.4882
  -2.000   0.3305   0.00816   0.00238  -0.1262   0.6682   0.5047
  -1.750   0.3574   0.00823   0.00237  -0.1259   0.6578   0.5188
  -1.500   0.3843   0.00828   0.00239  -0.1256   0.6475   0.5345
  -1.250   0.4114   0.00833   0.00240  -0.1254   0.6381   0.5474
  -1.000   0.4384   0.00842   0.00240  -0.1252   0.6294   0.5587
  -0.750   0.4658   0.00846   0.00243  -0.1251   0.6208   0.5701
  -0.500   0.4927   0.00853   0.00245  -0.1248   0.6130   0.5805
  -0.250   0.5200   0.00856   0.00248  -0.1247   0.6050   0.5914
   0.250   0.5744   0.00867   0.00256  -0.1244   0.5907   0.6143
   0.500   0.6014   0.00875   0.00260  -0.1242   0.5838   0.6254
   0.750   0.6287   0.00879   0.00266  -0.1241   0.5773   0.6373
   1.000   0.6558   0.00885   0.00272  -0.1239   0.5708   0.6506
   1.250   0.6828   0.00892   0.00279  -0.1238   0.5647   0.6646
   1.500   0.7097   0.00895   0.00286  -0.1236   0.5583   0.6791
   1.750   0.7366   0.00903   0.00295  -0.1234   0.5525   0.6948
   2.000   0.7634   0.00906   0.00304  -0.1232   0.5466   0.7127
   2.250   0.7898   0.00910   0.00314  -0.1229   0.5405   0.7327
   2.500   0.8161   0.00918   0.00325  -0.1225   0.5351   0.7571
   2.750   0.8417   0.00917   0.00337  -0.1220   0.5292   0.7859
   3.000   0.8663   0.00920   0.00348  -0.1213   0.5236   0.8209
   3.250   0.8889   0.00921   0.00360  -0.1201   0.5183   0.8657
   3.500   0.9093   0.00909   0.00366  -0.1182   0.5127   0.9452
   3.750   0.9413   0.00923   0.00374  -0.1192   0.5068   1.0000
   4.000   0.9684   0.00934   0.00387  -0.1192   0.5009   1.0000
   4.250   0.9951   0.00947   0.00399  -0.1190   0.4947   1.0000
   4.500   1.0215   0.00965   0.00412  -0.1189   0.4884   1.0000
   4.750   1.0475   0.00975   0.00425  -0.1186   0.4813   1.0000
   5.000   1.0732   0.00995   0.00439  -0.1183   0.4747   1.0000
   5.250   1.0991   0.01004   0.00454  -0.1179   0.4676   1.0000
   5.500   1.1242   0.01023   0.00469  -0.1175   0.4607   1.0000
   5.750   1.1497   0.01035   0.00485  -0.1171   0.4534   1.0000
   6.000   1.1741   0.01055   0.00502  -0.1166   0.4458   1.0000
   6.250   1.1991   0.01068   0.00521  -0.1161   0.4379   1.0000
   6.750   1.2472   0.01104   0.00559  -0.1148   0.4211   1.0000
   7.000   1.2704   0.01125   0.00580  -0.1140   0.4124   1.0000
   7.250   1.2935   0.01145   0.00601  -0.1132   0.4027   1.0000
   7.500   1.3164   0.01166   0.00625  -0.1124   0.3928   1.0000
   7.750   1.3379   0.01191   0.00650  -0.1113   0.3817   1.0000
   8.000   1.3583   0.01219   0.00677  -0.1100   0.3694   1.0000
   8.250   1.3777   0.01247   0.00705  -0.1086   0.3558   1.0000
   8.500   1.3955   0.01281   0.00737  -0.1068   0.3403   1.0000
   8.750   1.4129   0.01318   0.00773  -0.1050   0.3235   1.0000
   9.000   1.4290   0.01362   0.00813  -0.1031   0.3037   1.0000
   9.250   1.4415   0.01422   0.00863  -0.1006   0.2799   1.0000
   9.500   1.4518   0.01496   0.00924  -0.0978   0.2516   1.0000
   9.750   1.4588   0.01587   0.00999  -0.0946   0.2199   1.0000
  10.000   1.4638   0.01692   0.01086  -0.0912   0.1896   1.0000
  10.250   1.4683   0.01801   0.01182  -0.0879   0.1635   1.0000
  10.500   1.4724   0.01914   0.01283  -0.0846   0.1408   1.0000
  10.750   1.4777   0.02025   0.01386  -0.0817   0.1229   1.0000
  11.000   1.4832   0.02138   0.01494  -0.0789   0.1082   1.0000
  11.250   1.4882   0.02259   0.01612  -0.0763   0.0956   1.0000
  11.500   1.4921   0.02392   0.01742  -0.0737   0.0845   1.0000
  11.750   1.4950   0.02540   0.01888  -0.0713   0.0746   1.0000
  12.000   1.4994   0.02686   0.02036  -0.0692   0.0664   1.0000
  12.250   1.5023   0.02850   0.02202  -0.0671   0.0586   1.0000
  12.500   1.5032   0.03042   0.02394  -0.0652   0.0523   1.0000
  12.750   1.5069   0.03221   0.02578  -0.0637   0.0469   1.0000
  13.000   1.5071   0.03440   0.02799  -0.0622   0.0415   1.0000
  13.250   1.5081   0.03665   0.03027  -0.0610   0.0368   1.0000
  13.500   1.5081   0.03910   0.03277  -0.0599   0.0326   1.0000
  13.750   1.5063   0.04183   0.03553  -0.0591   0.0285   1.0000
  14.000   1.5046   0.04469   0.03846  -0.0584   0.0245   1.0000
  14.250   1.4988   0.04811   0.04191  -0.0579   0.0207   1.0000
  14.500   1.4948   0.05144   0.04532  -0.0576   0.0180   1.0000
  14.750   1.4879   0.05527   0.04922  -0.0575   0.0160   1.0000
  15.000   1.4845   0.05878   0.05281  -0.0575   0.0144   1.0000
  15.250   1.4759   0.06306   0.05717  -0.0578   0.0131   1.0000
  15.500   1.4701   0.06713   0.06135  -0.0583   0.0124   1.0000
  15.750   1.4668   0.07096   0.06528  -0.0589   0.0117   1.0000
  16.000   1.4626   0.07498   0.06941  -0.0596   0.0111   1.0000
  16.250   1.4576   0.07922   0.07374  -0.0605   0.0106   1.0000
  16.500   1.4495   0.08404   0.07865  -0.0617   0.0102   1.0000
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