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EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 377 (MODIFIED) AIRFOIL (e377m-il)
Reynolds number: 500,000
Max Cl/Cd: 117.67 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e377m-il-500000.txt
Download as CSV file: xf-e377m-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 377 (MODIFIED) AIRFOIL                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -6.500  -0.0957   0.08424   0.08148  -0.0370   0.7548   0.0084
  -6.250  -0.0837   0.08132   0.07848  -0.0379   0.7376   0.0086
  -6.000  -0.0688   0.07889   0.07597  -0.0397   0.7223   0.0087
  -5.500  -0.0343   0.07410   0.07105  -0.0441   0.6951   0.0092
  -5.250  -0.0149   0.07166   0.06854  -0.0467   0.6829   0.0095
  -5.000   0.0059   0.06919   0.06600  -0.0494   0.6721   0.0098
  -4.750   0.0281   0.06665   0.06339  -0.0524   0.6631   0.0104
  -1.750   0.3954   0.03672   0.03255  -0.0945   0.5810   0.0186
  -1.500   0.4245   0.03511   0.03085  -0.0963   0.5760   0.0202
  -1.250   0.4585   0.03343   0.02910  -0.0987   0.5705   0.0231
  -1.000   0.5010   0.03265   0.02815  -0.1018   0.5653   0.0251
  -0.750   0.5360   0.03113   0.02652  -0.1039   0.5603   0.0253
  -0.500   0.5696   0.02786   0.02315  -0.1066   0.5555   0.0262
  -0.250   0.5957   0.02648   0.02169  -0.1074   0.5509   0.0278
   0.000   0.6264   0.02532   0.02045  -0.1085   0.5461   0.0309
   0.250   0.6656   0.02513   0.02011  -0.1098   0.5409   0.0355
   0.750   0.7262   0.02136   0.01611  -0.1122   0.5324   0.0377
   1.000   0.7554   0.02040   0.01510  -0.1127   0.5275   0.0392
   1.250   0.7859   0.01945   0.01402  -0.1132   0.5230   0.0413
   1.500   0.8252   0.01657   0.01076  -0.1144   0.5193   0.0305
   1.750   0.8637   0.01157   0.00492  -0.1156   0.5156   0.0332
   2.000   0.8915   0.01101   0.00421  -0.1154   0.5109   0.0390
   2.250   0.9186   0.01146   0.00475  -0.1150   0.5065   0.0613
   2.500   0.9449   0.01251   0.00598  -0.1146   0.5018   0.0637
   2.750   0.9715   0.01283   0.00632  -0.1144   0.4970   0.0723
   3.000   0.9974   0.01329   0.00680  -0.1141   0.4925   0.0777
   3.250   1.0244   0.01325   0.00676  -0.1140   0.4879   0.0851
   3.500   1.0515   0.01309   0.00657  -0.1138   0.4830   0.0894
   3.750   1.0790   0.01281   0.00617  -0.1135   0.4783   0.0953
   4.000   1.1052   0.01288   0.00631  -0.1134   0.4729   0.1004
   4.250   1.1322   0.01348   0.00686  -0.1129   0.4670   0.1174
   4.500   1.1584   0.01286   0.00623  -0.1130   0.4617   0.1196
   4.750   1.1851   0.01269   0.00611  -0.1129   0.4555   0.1229
   5.000   1.2119   0.01274   0.00609  -0.1125   0.4499   0.1302
   5.250   1.2382   0.01254   0.00597  -0.1124   0.4440   0.1341
   5.500   1.2648   0.01255   0.00595  -0.1121   0.4377   0.1423
   5.750   1.2909   0.01245   0.00589  -0.1119   0.4313   0.1453
   6.000   1.3173   0.01256   0.00600  -0.1116   0.4241   0.1532
   6.250   1.3431   0.01244   0.00595  -0.1114   0.4171   0.1557
   6.500   1.3692   0.01252   0.00605  -0.1111   0.4090   0.1654
   6.750   1.3949   0.01246   0.00607  -0.1109   0.4008   0.1719
   7.250   1.4459   0.01264   0.00632  -0.1103   0.3813   0.2002
   7.500   1.4719   0.01256   0.00624  -0.1097   0.3716   0.1392
   7.750   1.4968   0.01272   0.00642  -0.1093   0.3574   0.1402
   8.000   1.5205   0.01296   0.00663  -0.1089   0.3343   0.1433
   8.250   1.5428   0.01345   0.00700  -0.1083   0.2967   0.1463
   8.500   1.5623   0.01435   0.00762  -0.1075   0.2453   0.1479
   8.750   1.5790   0.01560   0.00857  -0.1064   0.1898   0.1496
   9.000   1.5964   0.01672   0.00946  -0.1054   0.1506   0.1513
   9.250   1.6132   0.01781   0.01037  -0.1043   0.1168   0.1528
   9.500   1.6277   0.01906   0.01142  -0.1030   0.0825   0.1547
   9.750   1.6388   0.02058   0.01271  -0.1012   0.0486   0.1566
  10.000   1.6423   0.02266   0.01452  -0.0986   0.0147   0.1584
  10.250   1.6506   0.02406   0.01594  -0.0963   0.0080   0.1614
  10.500   1.6589   0.02527   0.01726  -0.0940   0.0066   0.1641
  10.750   1.6607   0.02650   0.01862  -0.0907   0.0058   0.1664
  11.000   1.6588   0.02813   0.02041  -0.0875   0.0054   0.1681
  11.250   1.6575   0.03002   0.02244  -0.0851   0.0052   0.1697
  11.500   1.6568   0.03213   0.02470  -0.0834   0.0052   0.1716
  11.750   1.6553   0.03459   0.02729  -0.0821   0.0050   0.1733
  12.000   1.6530   0.03737   0.03022  -0.0811   0.0049   0.1752
  12.250   1.6491   0.04055   0.03353  -0.0805   0.0046   0.1765
  12.500   1.6446   0.04396   0.03708  -0.0802   0.0045   0.1782
  12.750   1.6392   0.04761   0.04087  -0.0801   0.0045   0.1801
  13.000   1.6325   0.05156   0.04495  -0.0801   0.0043   0.1820
  13.250   1.6255   0.05564   0.04916  -0.0803   0.0042   0.1840
  13.500   1.6176   0.05997   0.05362  -0.0807   0.0042   0.1859
  13.750   1.6100   0.06432   0.05810  -0.0812   0.0041   0.1879
  14.000   1.6020   0.06890   0.06281  -0.0819   0.0040   0.1904
  14.250   1.5938   0.07367   0.06771  -0.0828   0.0040   0.1934
  14.500   1.5867   0.07843   0.07259  -0.0837   0.0039   0.1968
  14.750   1.5801   0.08319   0.07751  -0.0848   0.0039   0.2002
  15.000   1.5741   0.08799   0.08244  -0.0859   0.0039   0.2042
  15.250   1.5684   0.09283   0.08743  -0.0870   0.0039   0.2090
  16.750   1.3177   0.13632   0.13255  -0.0975   0.0043   0.2121
  17.000   1.3055   0.14147   0.13786  -0.0999   0.0042   0.2162
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