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EPPLER 379 AIRFOIL (e379-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 379 AIRFOIL (e379-il)
Reynolds number: 200,000
Max Cl/Cd: 117.83 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e379-il-200000.txt
Download as CSV file: xf-e379-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 379 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1487   0.09831   0.09510  -0.0235   0.8365   0.0035
  -7.750  -0.1412   0.09624   0.09294  -0.0239   0.8144   0.0036
  -7.500  -0.1337   0.09432   0.09093  -0.0243   0.7967   0.0036
  -7.250  -0.1246   0.09233   0.08887  -0.0252   0.7815   0.0036
  -7.000  -0.1130   0.09008   0.08655  -0.0267   0.7677   0.0037
  -6.750  -0.1003   0.08785   0.08426  -0.0283   0.7555   0.0038
  -6.500  -0.0862   0.08554   0.08190  -0.0303   0.7439   0.0039
  -6.250  -0.0709   0.08319   0.07949  -0.0324   0.7334   0.0040
  -6.000  -0.0545   0.08079   0.07704  -0.0348   0.7240   0.0042
  -5.750  -0.0371   0.07846   0.07464  -0.0372   0.7157   0.0043
  -5.500  -0.0180   0.07605   0.07220  -0.0399   0.7065   0.0045
  -5.250   0.0023   0.07367   0.06976  -0.0427   0.6990   0.0046
  -5.000   0.0250   0.07134   0.06738  -0.0458   0.6914   0.0050
  -4.750   0.0515   0.06939   0.06538  -0.0495   0.6841   0.0053
  -4.500   0.0862   0.06861   0.06443  -0.0549   0.6770   0.0057
  -4.250   0.1281   0.06850   0.06422  -0.0620   0.6693   0.0059
  -4.000   0.1548   0.06536   0.06101  -0.0654   0.6636   0.0060
  -3.750   0.1603   0.05945   0.05515  -0.0643   0.6581   0.0065
  -3.500   0.1809   0.05626   0.05191  -0.0663   0.6521   0.0073
  -3.250   0.2086   0.05379   0.04936  -0.0694   0.6466   0.0088
  -3.000   0.2396   0.05145   0.04696  -0.0730   0.6405   0.0095
  -2.750   0.2711   0.04926   0.04465  -0.0763   0.6358   0.0101
   0.000   0.6364   0.03014   0.02426  -0.1037   0.5808   0.0214
   0.250   0.6710   0.02934   0.02336  -0.1049   0.5756   0.0242
   0.500   0.7099   0.03004   0.02378  -0.1054   0.5714   0.0256
   0.750   0.7356   0.02681   0.02046  -0.1070   0.5677   0.0279
   1.000   0.7650   0.02557   0.01911  -0.1078   0.5625   0.0333
   1.250   0.8026   0.02675   0.01995  -0.1075   0.5582   0.0379
   1.500   0.8268   0.02374   0.01691  -0.1089   0.5548   0.0450
   1.750   0.8597   0.02344   0.01646  -0.1090   0.5499   0.0513
   2.000   0.8871   0.02215   0.01508  -0.1095   0.5457   0.0578
   2.250   0.9169   0.02146   0.01415  -0.1095   0.5423   0.0665
   2.500   0.9477   0.02185   0.01446  -0.1092   0.5371   0.0876
   2.750   0.9748   0.02019   0.01277  -0.1097   0.5329   0.1026
   3.000   1.0032   0.01964   0.01201  -0.1095   0.5295   0.1274
   3.250   1.0307   0.01898   0.01135  -0.1096   0.5249   0.1558
   3.500   1.0632   0.01841   0.01041  -0.1083   0.5208   0.0484
   3.750   0.9497   0.00806   0.00085  -0.1102   0.5264   0.0255
   4.000   1.1188   0.01726   0.00890  -0.1073   0.5133   0.0250
   4.250   1.1457   0.01693   0.00853  -0.1071   0.5083   0.0238
   4.500   1.1732   0.01679   0.00821  -0.1068   0.5042   0.0459
   4.750   1.2060   0.01602   0.00840  -0.1081   0.4997   1.0000
   5.000   1.2318   0.01625   0.00858  -0.1079   0.4943   1.0000
   5.250   1.2581   0.01639   0.00860  -0.1076   0.4900   1.0000
   5.500   1.2835   0.01666   0.00889  -0.1075   0.4844   1.0000
   5.750   1.3066   0.01503   0.00691  -0.1058   0.4497   1.0000
   6.000   1.3308   0.01479   0.00669  -0.1052   0.4283   1.0000
   6.250   1.3541   0.01473   0.00644  -0.1046   0.3973   1.0000
   6.500   1.3763   0.01501   0.00648  -0.1041   0.3569   1.0000
   6.750   1.3997   0.01538   0.00677  -0.1037   0.3357   1.0000
   7.000   1.4227   0.01581   0.00714  -0.1033   0.3154   1.0000
   7.250   1.4455   0.01628   0.00759  -0.1028   0.2959   1.0000
   7.500   1.4683   0.01674   0.00808  -0.1024   0.2806   1.0000
   7.750   1.4772   0.01880   0.00949  -0.1010   0.1908   1.0000
   8.000   1.4708   0.02241   0.01215  -0.0983   0.0711   1.0000
   8.250   1.4700   0.02495   0.01427  -0.0958   0.0125   1.0000
   8.500   1.4828   0.02602   0.01530  -0.0943   0.0111   1.0000
   8.750   1.4987   0.02674   0.01623  -0.0931   0.0098   1.0000
   9.000   1.5083   0.02779   0.01745  -0.0912   0.0098   1.0000
   9.250   1.5143   0.02908   0.01892  -0.0892   0.0099   1.0000
   9.750   1.5093   0.03440   0.02574  -0.0853   0.0084   1.0000
  10.000   1.5075   0.03733   0.02897  -0.0842   0.0091   1.0000
  10.250   1.5065   0.04029   0.03217  -0.0835   0.0098   1.0000
  10.500   1.5042   0.04346   0.03553  -0.0829   0.0100   1.0000
  10.750   1.4995   0.04708   0.03939  -0.0826   0.0108   1.0000
  11.000   1.4940   0.05080   0.04328  -0.0824   0.0110   1.0000
  11.250   1.4859   0.05496   0.04762  -0.0823   0.0116   1.0000
  11.500   1.4784   0.05907   0.05188  -0.0822   0.0118   1.0000
  11.750   1.4712   0.06315   0.05610  -0.0821   0.0122   1.0000
  12.000   1.4642   0.06721   0.06028  -0.0819   0.0126   1.0000
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