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E214 (11.1%) (e214-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E214 (11.1%) (e214-il)
Reynolds number: 200,000
Max Cl/Cd: 87.57 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e214-il-200000.txt
Download as CSV file: xf-e214-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E214  (11.1%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3994   0.09492   0.09184  -0.0316   1.0000   0.0491
  -7.750  -0.4037   0.09317   0.09013  -0.0295   1.0000   0.0500
  -7.500  -0.4127   0.09147   0.08848  -0.0274   1.0000   0.0510
  -7.250  -0.4115   0.08859   0.08564  -0.0289   0.9977   0.0524
  -7.000  -0.3994   0.08393   0.08098  -0.0358   0.9912   0.0550
  -6.750  -0.3698   0.06968   0.06637  -0.0707   0.9760   0.0592
  -6.500  -0.3546   0.06277   0.05957  -0.0733   0.9730   0.0609
  -6.250  -0.3342   0.06055   0.05739  -0.0736   0.9677   0.0628
  -6.000  -0.3073   0.05609   0.05281  -0.0794   0.9619   0.0667
  -5.750  -0.2779   0.04767   0.04382  -0.0911   0.9543   0.0747
  -5.500  -0.2493   0.04490   0.04104  -0.0933   0.9497   0.0779
  -5.250  -0.2106   0.04042   0.03616  -0.0999   0.9466   0.0898
  -5.000  -0.1599   0.02772   0.02173  -0.1059   0.9458   0.0441
  -4.750  -0.1320   0.02493   0.01849  -0.1064   0.9386   0.0426
  -4.500  -0.0927   0.02279   0.01595  -0.1087   0.9355   0.0430
  -4.250  -0.0513   0.02146   0.01433  -0.1113   0.9333   0.0453
  -4.000  -0.0208   0.02029   0.01297  -0.1117   0.9268   0.0461
  -3.750   0.0159   0.01888   0.01145  -0.1133   0.9229   0.0477
  -3.500   0.0560   0.01758   0.01019  -0.1158   0.9203   0.0513
  -3.250   0.0990   0.01684   0.00939  -0.1187   0.9183   0.0589
  -3.000   0.1271   0.01601   0.00859  -0.1189   0.9098   0.0705
  -2.750   0.1697   0.01435   0.00767  -0.1226   0.9073   0.2290
  -2.500   0.2120   0.01324   0.00739  -0.1261   0.9053   0.4535
  -2.250   0.2422   0.01301   0.00737  -0.1262   0.8981   0.5578
  -2.000   0.2801   0.01276   0.00720  -0.1277   0.8939   0.6212
  -1.750   0.3216   0.01247   0.00691  -0.1299   0.8912   0.6561
  -1.500   0.3512   0.01233   0.00677  -0.1298   0.8831   0.6832
  -1.250   0.3887   0.01207   0.00648  -0.1313   0.8783   0.7092
  -1.000   0.4216   0.01186   0.00626  -0.1318   0.8715   0.7293
  -0.750   0.4547   0.01164   0.00603  -0.1324   0.8641   0.7492
  -0.500   0.4860   0.01147   0.00585  -0.1328   0.8559   0.7691
  -0.250   0.5189   0.01124   0.00561  -0.1333   0.8483   0.7872
   0.000   0.5455   0.01112   0.00550  -0.1326   0.8378   0.8055
   0.250   0.5754   0.01096   0.00534  -0.1326   0.8288   0.8250
   0.500   0.6037   0.01080   0.00517  -0.1323   0.8191   0.8451
   0.750   0.6264   0.01070   0.00509  -0.1308   0.8075   0.8674
   1.000   0.6489   0.01058   0.00498  -0.1292   0.7964   0.8935
   1.500   0.7144   0.01027   0.00462  -0.1307   0.7752   1.0000
   1.750   0.7470   0.01037   0.00464  -0.1321   0.7629   1.0000
   2.000   0.7782   0.01050   0.00468  -0.1331   0.7508   1.0000
   2.250   0.8084   0.01064   0.00474  -0.1336   0.7390   1.0000
   2.500   0.8381   0.01078   0.00480  -0.1341   0.7274   1.0000
   2.750   0.8676   0.01094   0.00487  -0.1344   0.7158   1.0000
   3.000   0.8944   0.01111   0.00502  -0.1342   0.7031   1.0000
   3.250   0.9209   0.01129   0.00516  -0.1339   0.6901   1.0000
   3.500   0.9473   0.01147   0.00531  -0.1336   0.6772   1.0000
   3.750   0.9736   0.01167   0.00547  -0.1333   0.6642   1.0000
   4.000   0.9995   0.01186   0.00565  -0.1329   0.6511   1.0000
   4.250   1.0251   0.01206   0.00583  -0.1324   0.6376   1.0000
   4.500   1.0502   0.01225   0.00601  -0.1318   0.6234   1.0000
   4.750   1.0747   0.01246   0.00620  -0.1310   0.6086   1.0000
   5.000   1.0987   0.01266   0.00642  -0.1302   0.5935   1.0000
   5.250   1.1224   0.01288   0.00664  -0.1294   0.5780   1.0000
   5.500   1.1456   0.01310   0.00687  -0.1284   0.5618   1.0000
   5.750   1.1682   0.01334   0.00710  -0.1273   0.5447   1.0000
   6.000   1.1903   0.01361   0.00736  -0.1261   0.5267   1.0000
   6.250   1.2114   0.01388   0.00764  -0.1248   0.5073   1.0000
   6.500   1.2317   0.01418   0.00794  -0.1233   0.4866   1.0000
   6.750   1.2513   0.01452   0.00827  -0.1218   0.4650   1.0000
   7.000   1.2695   0.01490   0.00864  -0.1199   0.4406   1.0000
   7.250   1.2866   0.01533   0.00904  -0.1179   0.4139   1.0000
   7.500   1.3018   0.01584   0.00948  -0.1157   0.3844   1.0000
   7.750   1.3152   0.01645   0.00999  -0.1132   0.3525   1.0000
   8.000   1.3268   0.01714   0.01058  -0.1104   0.3183   1.0000
   8.250   1.3353   0.01793   0.01125  -0.1071   0.2831   1.0000
   8.500   1.3421   0.01888   0.01203  -0.1037   0.2478   1.0000
   8.750   1.3486   0.01992   0.01293  -0.1004   0.2132   1.0000
   9.000   1.3538   0.02111   0.01395  -0.0970   0.1814   1.0000
   9.250   1.3587   0.02239   0.01508  -0.0938   0.1532   1.0000
   9.500   1.3638   0.02372   0.01629  -0.0907   0.1285   1.0000
   9.750   1.3683   0.02513   0.01760  -0.0878   0.1079   1.0000
  10.000   1.3736   0.02654   0.01895  -0.0851   0.0904   1.0000
  10.250   1.3781   0.02805   0.02045  -0.0824   0.0766   1.0000
  10.500   1.3823   0.02966   0.02206  -0.0799   0.0654   1.0000
  10.750   1.3848   0.03147   0.02390  -0.0773   0.0561   1.0000
  11.000   1.3845   0.03357   0.02600  -0.0747   0.0477   1.0000
  11.250   1.3835   0.03585   0.02828  -0.0724   0.0400   1.0000
  11.500   1.3857   0.03799   0.03055  -0.0704   0.0340   1.0000
  11.750   1.3785   0.04111   0.03367  -0.0681   0.0305   1.0000
  12.000   1.3803   0.04357   0.03629  -0.0664   0.0277   1.0000
  12.250   1.3820   0.04609   0.03891  -0.0650   0.0255   1.0000
  12.500   1.3820   0.04888   0.04176  -0.0638   0.0240   1.0000
  12.750   1.3810   0.05228   0.04520  -0.0622   0.0225   1.0000
  13.000   1.3863   0.05467   0.04782  -0.0614   0.0214   1.0000
  13.250   1.3902   0.05728   0.05059  -0.0607   0.0201   1.0000
  13.500   1.3931   0.06005   0.05349  -0.0601   0.0191   1.0000
  13.750   1.3956   0.06296   0.05651  -0.0597   0.0183   1.0000
  14.000   1.3984   0.06602   0.05967  -0.0592   0.0177   1.0000
  14.250   1.4017   0.06937   0.06314  -0.0586   0.0172   1.0000
  14.500   1.4033   0.07362   0.06761  -0.0579   0.0168   1.0000
  14.750   1.3989   0.07814   0.07238  -0.0580   0.0166   1.0000
  15.000   1.3915   0.08274   0.07724  -0.0586   0.0165   1.0000
  15.250   1.3821   0.08776   0.08252  -0.0596   0.0164   1.0000
  15.500   1.3710   0.09322   0.08824  -0.0610   0.0164   1.0000
  15.750   1.3580   0.09915   0.09441  -0.0631   0.0163   1.0000
  16.000   1.3436   0.10551   0.10101  -0.0657   0.0163   1.0000
  16.250   1.3284   0.11227   0.10800  -0.0688   0.0164   1.0000
  16.500   1.3122   0.11950   0.11545  -0.0726   0.0164   1.0000
  16.750   1.2953   0.12719   0.12335  -0.0770   0.0165   1.0000
  17.000   1.2781   0.13531   0.13165  -0.0819   0.0166   1.0000
  17.250   1.2635   0.14323   0.13977  -0.0871   0.0167   1.0000
  17.500   1.2498   0.15138   0.14809  -0.0929   0.0168   1.0000
  17.750   1.2329   0.16116   0.15807  -0.1002   0.0171   1.0000
  18.000   1.1171   0.21498   0.21208  -0.1328   0.0242   1.0000
  18.250   1.1274   0.21543   0.21257  -0.1333   0.0233   1.0000
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