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E214 (11.1%) (e214-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E214 (11.1%) (e214-il)
Reynolds number: 500,000
Max Cl/Cd: 111.28 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e214-il-500000-n5.txt
Download as CSV file: xf-e214-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3500   0.09603   0.09371  -0.0530   0.9939   0.0081
 -10.000  -0.3452   0.09101   0.08870  -0.0569   0.9916   0.0083
  -9.500  -0.4718   0.03703   0.03433  -0.1087   0.9681   0.0083
  -9.250  -0.4568   0.03340   0.03046  -0.1132   0.9625   0.0085
  -9.000  -0.4338   0.03008   0.02683  -0.1175   0.9598   0.0087
  -8.750  -0.4117   0.02950   0.02621  -0.1178   0.9553   0.0091
  -8.500  -0.3889   0.02787   0.02437  -0.1192   0.9511   0.0095
  -8.250  -0.3640   0.02486   0.02098  -0.1218   0.9483   0.0101
  -8.000  -0.3360   0.02215   0.01784  -0.1242   0.9464   0.0108
  -7.750  -0.3146   0.02045   0.01584  -0.1242   0.9411   0.0112
  -7.500  -0.2868   0.01910   0.01423  -0.1251   0.9376   0.0115
  -7.250  -0.2561   0.01754   0.01239  -0.1267   0.9351   0.0119
  -7.000  -0.2231   0.01627   0.01099  -0.1287   0.9332   0.0126
  -6.750  -0.1933   0.01566   0.01032  -0.1295   0.9294   0.0132
  -6.500  -0.1645   0.01499   0.00955  -0.1301   0.9246   0.0139
  -6.250  -0.1310   0.01415   0.00857  -0.1317   0.9214   0.0145
  -6.000  -0.0958   0.01336   0.00766  -0.1336   0.9187   0.0150
  -5.750  -0.0678   0.01274   0.00693  -0.1338   0.9126   0.0154
  -5.500  -0.0351   0.01217   0.00627  -0.1351   0.9076   0.0159
  -5.250  -0.0013   0.01178   0.00579  -0.1365   0.9029   0.0164
  -5.000   0.0272   0.01099   0.00493  -0.1370   0.8954   0.0173
  -4.750   0.0603   0.01049   0.00435  -0.1383   0.8893   0.0181
  -4.500   0.0891   0.01014   0.00393  -0.1386   0.8805   0.0188
  -4.250   0.1198   0.00983   0.00355  -0.1393   0.8723   0.0197
  -4.000   0.1498   0.00957   0.00321  -0.1398   0.8629   0.0205
  -3.750   0.1786   0.00936   0.00292  -0.1400   0.8522   0.0214
  -3.500   0.2076   0.00918   0.00266  -0.1402   0.8411   0.0227
  -3.250   0.2363   0.00898   0.00240  -0.1404   0.8290   0.0266
  -3.000   0.2647   0.00879   0.00219  -0.1406   0.8163   0.0376
  -2.750   0.2925   0.00857   0.00202  -0.1407   0.8029   0.0697
  -2.500   0.3200   0.00838   0.00188  -0.1407   0.7893   0.1077
  -2.250   0.3473   0.00820   0.00178  -0.1407   0.7755   0.1535
  -2.000   0.3744   0.00798   0.00169  -0.1408   0.7620   0.2180
  -1.750   0.4014   0.00774   0.00162  -0.1409   0.7489   0.2977
  -1.500   0.4284   0.00741   0.00160  -0.1410   0.7361   0.4179
  -1.250   0.4553   0.00731   0.00164  -0.1409   0.7240   0.4969
  -1.000   0.4820   0.00732   0.00167  -0.1407   0.7121   0.5349
  -0.750   0.5088   0.00737   0.00169  -0.1404   0.7008   0.5560
  -0.500   0.5355   0.00743   0.00171  -0.1401   0.6892   0.5719
  -0.250   0.5623   0.00748   0.00174  -0.1399   0.6780   0.5874
   0.000   0.5890   0.00754   0.00178  -0.1396   0.6671   0.6024
   0.250   0.6156   0.00761   0.00182  -0.1393   0.6565   0.6167
   0.500   0.6420   0.00768   0.00187  -0.1390   0.6455   0.6302
   0.750   0.6687   0.00775   0.00193  -0.1387   0.6349   0.6438
   1.000   0.6951   0.00782   0.00200  -0.1384   0.6245   0.6576
   1.250   0.7214   0.00790   0.00207  -0.1381   0.6141   0.6721
   1.500   0.7476   0.00798   0.00215  -0.1378   0.6032   0.6864
   1.750   0.7739   0.00806   0.00224  -0.1374   0.5921   0.6996
   2.000   0.7998   0.00816   0.00233  -0.1370   0.5806   0.7123
   2.500   0.8509   0.00837   0.00254  -0.1361   0.5559   0.7403
   3.000   0.9011   0.00859   0.00280  -0.1350   0.5300   0.7743
   3.250   0.9257   0.00870   0.00293  -0.1343   0.5165   0.7947
   3.500   0.9495   0.00882   0.00308  -0.1335   0.5020   0.8188
   3.750   0.9717   0.00895   0.00324  -0.1323   0.4859   0.8500
   4.000   0.9907   0.00903   0.00338  -0.1303   0.4696   0.8972
   4.250   1.0138   0.00911   0.00348  -0.1293   0.4533   1.0000
   4.500   1.0384   0.00935   0.00367  -0.1288   0.4356   1.0000
   4.750   1.0624   0.00962   0.00388  -0.1281   0.4167   1.0000
   5.000   1.0856   0.00994   0.00411  -0.1273   0.3948   1.0000
   5.250   1.1081   0.01030   0.00437  -0.1265   0.3700   1.0000
   5.500   1.1309   0.01065   0.00463  -0.1256   0.3474   1.0000
   5.750   1.1527   0.01105   0.00493  -0.1247   0.3226   1.0000
   6.000   1.1738   0.01151   0.00528  -0.1236   0.2954   1.0000
   6.250   1.1940   0.01202   0.00566  -0.1223   0.2657   1.0000
   6.500   1.2130   0.01260   0.00608  -0.1209   0.2328   1.0000
   6.750   1.2310   0.01323   0.00655  -0.1194   0.2003   1.0000
   7.000   1.2498   0.01379   0.00700  -0.1179   0.1759   1.0000
   7.250   1.2676   0.01434   0.00747  -0.1163   0.1554   1.0000
   7.500   1.2843   0.01492   0.00796  -0.1145   0.1334   1.0000
   7.750   1.2994   0.01560   0.00852  -0.1124   0.1107   1.0000
   8.000   1.3141   0.01629   0.00910  -0.1103   0.0907   1.0000
   8.250   1.3288   0.01697   0.00970  -0.1082   0.0732   1.0000
   8.500   1.3432   0.01766   0.01032  -0.1062   0.0593   1.0000
   8.750   1.3583   0.01831   0.01095  -0.1042   0.0496   1.0000
   9.000   1.3725   0.01900   0.01162  -0.1022   0.0409   1.0000
   9.250   1.3864   0.01972   0.01232  -0.1002   0.0338   1.0000
   9.500   1.4008   0.02041   0.01303  -0.0983   0.0286   1.0000
   9.750   1.4135   0.02121   0.01383  -0.0962   0.0231   1.0000
  10.000   1.4248   0.02210   0.01473  -0.0939   0.0180   1.0000
  10.250   1.4355   0.02305   0.01570  -0.0917   0.0133   1.0000
  10.500   1.4455   0.02408   0.01674  -0.0895   0.0097   1.0000
  10.750   1.4551   0.02515   0.01786  -0.0873   0.0075   1.0000
  11.000   1.4644   0.02627   0.01905  -0.0852   0.0065   1.0000
  11.250   1.4740   0.02741   0.02027  -0.0832   0.0058   1.0000
  11.500   1.4828   0.02864   0.02158  -0.0813   0.0054   1.0000
  11.750   1.4905   0.03000   0.02303  -0.0793   0.0050   1.0000
  12.000   1.4961   0.03158   0.02470  -0.0773   0.0046   1.0000
  12.250   1.5015   0.03323   0.02646  -0.0755   0.0044   1.0000
  12.500   1.5076   0.03488   0.02823  -0.0739   0.0042   1.0000
  12.750   1.5126   0.03669   0.03015  -0.0723   0.0042   1.0000
  13.000   1.5164   0.03867   0.03225  -0.0709   0.0040   1.0000
  13.250   1.5197   0.04080   0.03450  -0.0696   0.0039   1.0000
  13.500   1.5219   0.04311   0.03693  -0.0685   0.0038   1.0000
  13.750   1.5237   0.04557   0.03950  -0.0676   0.0036   1.0000
  14.000   1.5248   0.04820   0.04224  -0.0669   0.0035   1.0000
  14.250   1.5245   0.05110   0.04526  -0.0663   0.0034   1.0000
  14.500   1.5237   0.05417   0.04846  -0.0660   0.0033   1.0000
  14.750   1.5216   0.05754   0.05195  -0.0659   0.0032   1.0000
  15.000   1.5180   0.06124   0.05577  -0.0660   0.0031   1.0000
  15.250   1.5124   0.06535   0.06002  -0.0664   0.0030   1.0000
  15.500   1.5052   0.06988   0.06468  -0.0672   0.0029   1.0000
  15.750   1.4959   0.07490   0.06985  -0.0683   0.0029   1.0000
  16.000   1.4867   0.08012   0.07524  -0.0697   0.0028   1.0000
  16.250   1.4755   0.08584   0.08110  -0.0715   0.0028   1.0000
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