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EPPLER 376 AIRFOIL (e376-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 376 AIRFOIL (e376-il)
Reynolds number: 200,000
Max Cl/Cd: 92.65 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e376-il-200000.txt
Download as CSV file: xf-e376-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 376 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1709   0.09802   0.09517  -0.0174   1.0000   0.0097
  -8.500  -0.1632   0.09591   0.09312  -0.0187   1.0000   0.0097
  -8.250  -0.1562   0.09400   0.09129  -0.0200   1.0000   0.0097
  -8.000  -0.1453   0.09189   0.08924  -0.0228   0.9855   0.0098
  -3.250   0.2084   0.05377   0.04948  -0.0774   0.7046   0.0154
  -3.000   0.2297   0.05058   0.04620  -0.0790   0.6972   0.0159
  -2.750   0.2580   0.04814   0.04370  -0.0819   0.6885   0.0167
  -2.500   0.2891   0.04597   0.04140  -0.0850   0.6809   0.0176
  -2.250   0.3221   0.04388   0.03921  -0.0883   0.6733   0.0188
  -2.000   0.3569   0.04195   0.03717  -0.0916   0.6664   0.0205
  -1.750   0.4149   0.04351   0.03844  -0.0974   0.6584   0.0228
  -1.500   0.4497   0.04127   0.03608  -0.1003   0.6520   0.0231
  -1.250   0.4665   0.03665   0.03148  -0.1012   0.6458   0.0242
  -1.000   0.4954   0.03464   0.02933  -0.1031   0.6402   0.0255
  -0.750   0.5278   0.03304   0.02767  -0.1052   0.6332   0.0272
  -0.500   0.5611   0.03167   0.02612  -0.1071   0.6278   0.0292
  -0.250   0.5965   0.03070   0.02506  -0.1090   0.6214   0.0318
   0.000   0.6385   0.03145   0.02555  -0.1106   0.6156   0.0333
   0.250   0.6720   0.02979   0.02375  -0.1122   0.6101   0.0338
   0.500   0.6960   0.02675   0.02071  -0.1136   0.6043   0.0358
   0.750   0.7258   0.02554   0.01936  -0.1145   0.5995   0.0387
   1.000   0.7584   0.02478   0.01850  -0.1154   0.5938   0.0433
   1.250   0.7931   0.02410   0.01762  -0.1161   0.5883   0.0470
   1.500   0.8203   0.02279   0.01620  -0.1168   0.5838   0.0525
   1.750   0.8560   0.02364   0.01683  -0.1165   0.5777   0.0581
   2.000   0.8824   0.02133   0.01449  -0.1176   0.5729   0.0610
   2.250   0.9111   0.02069   0.01374  -0.1178   0.5681   0.0664
   2.500   0.9420   0.02026   0.01318  -0.1178   0.5624   0.0722
   2.750   0.9697   0.01952   0.01233  -0.1180   0.5578   0.0773
   3.000   0.9993   0.01914   0.01184  -0.1178   0.5527   0.0851
   3.250   1.0274   0.01853   0.01117  -0.1178   0.5472   0.0887
   3.500   1.0550   0.01818   0.01067  -0.1177   0.5429   0.1135
   3.750   1.0874   0.01652   0.00860  -0.1169   0.5381   0.0548
   4.000   1.1147   0.01604   0.00798  -0.1165   0.5327   0.0718
   4.250   1.1408   0.01641   0.00835  -0.1163   0.5282   0.1140
   4.500   1.1672   0.01632   0.00827  -0.1160   0.5221   0.1227
   4.750   1.1936   0.01628   0.00821  -0.1157   0.5166   0.1328
   5.000   1.2202   0.01632   0.00830  -0.1155   0.5111   0.1483
   5.250   1.2461   0.01632   0.00836  -0.1151   0.5042   0.1697
   5.500   1.2726   0.01637   0.00831  -0.1148   0.4991   0.1967
   5.750   1.2983   0.01644   0.00854  -0.1146   0.4917   0.2382
   6.000   1.3265   0.01575   0.00856  -0.1147   0.4859   1.0000
   6.250   1.3517   0.01593   0.00887  -0.1143   0.4777   1.0000
   6.500   1.3776   0.01607   0.00890  -0.1138   0.4713   1.0000
   6.750   1.4024   0.01623   0.00921  -0.1134   0.4625   1.0000
   7.000   1.4277   0.01637   0.00935  -0.1129   0.4550   1.0000
   7.250   1.4526   0.01647   0.00954  -0.1124   0.4457   1.0000
   7.500   1.4771   0.01660   0.00979  -0.1119   0.4357   1.0000
   7.750   1.5017   0.01672   0.01005  -0.1113   0.4256   1.0000
   8.000   1.5259   0.01683   0.01023  -0.1107   0.4143   1.0000
   8.250   1.5494   0.01693   0.01047  -0.1100   0.3996   1.0000
   8.500   1.5714   0.01696   0.01057  -0.1091   0.3740   1.0000
   8.750   1.5925   0.01724   0.01089  -0.1082   0.3417   1.0000
   9.000   1.6099   0.01798   0.01149  -0.1070   0.2898   1.0000
   9.250   1.6229   0.01940   0.01258  -0.1056   0.2272   1.0000
   9.500   1.6307   0.02142   0.01421  -0.1038   0.1671   1.0000
   9.750   1.6350   0.02370   0.01613  -0.1018   0.1124   1.0000
  10.000   1.6302   0.02663   0.01861  -0.0988   0.0546   1.0000
  10.250   1.6178   0.02966   0.02140  -0.0948   0.0269   1.0000
  10.500   1.6066   0.03236   0.02416  -0.0913   0.0214   1.0000
  10.750   1.6011   0.03502   0.02701  -0.0892   0.0195   1.0000
  11.000   1.5963   0.03797   0.03015  -0.0879   0.0182   1.0000
  11.250   1.5913   0.04119   0.03355  -0.0870   0.0171   1.0000
  11.500   1.5858   0.04468   0.03718  -0.0865   0.0159   1.0000
  11.750   1.5781   0.04859   0.04121  -0.0862   0.0148   1.0000
  12.000   1.5671   0.05304   0.04580  -0.0861   0.0140   1.0000
  12.250   1.5555   0.05766   0.05059  -0.0860   0.0135   1.0000
  12.500   1.5476   0.06184   0.05489  -0.0857   0.0131   1.0000
  12.750   1.5443   0.06545   0.05864  -0.0854   0.0129   1.0000
  13.000   1.5419   0.06896   0.06230  -0.0848   0.0126   1.0000
  13.250   1.5409   0.07235   0.06584  -0.0841   0.0124   1.0000
  13.500   1.5413   0.07564   0.06928  -0.0833   0.0122   1.0000
  13.750   1.5425   0.07899   0.07281  -0.0824   0.0120   1.0000
  14.000   1.5431   0.08263   0.07666  -0.0817   0.0120   1.0000
  14.250   1.5417   0.08674   0.08100  -0.0813   0.0120   1.0000
  14.500   1.5378   0.09142   0.08592  -0.0815   0.0120   1.0000
  14.750   1.5308   0.09665   0.09141  -0.0824   0.0121   1.0000
  15.000   1.5216   0.10239   0.09740  -0.0839   0.0122   1.0000
  15.250   1.5105   0.10857   0.10382  -0.0860   0.0123   1.0000
  15.500   1.4981   0.11513   0.11062  -0.0886   0.0124   1.0000
  15.750   1.4850   0.12203   0.11775  -0.0918   0.0125   1.0000
  16.000   1.4712   0.12929   0.12522  -0.0955   0.0126   1.0000
  16.250   1.4572   0.13695   0.13309  -0.0999   0.0127   1.0000
  16.500   1.4428   0.14499   0.14131  -0.1047   0.0128   1.0000
  16.750   1.4287   0.15326   0.14977  -0.1099   0.0129   1.0000
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