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EPPLER 378 AIRFOIL (e378-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 378 AIRFOIL (e378-il)
Reynolds number: 500,000
Max Cl/Cd: 37.12 at α=13.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e378-il-500000.txt
Download as CSV file: xf-e378-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 378 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2967   0.12763   0.12480  -0.0143   0.8167   0.0074
  -9.750  -0.2899   0.12435   0.12152  -0.0141   0.8182   0.0075
  -9.500  -0.2808   0.12155   0.11871  -0.0153   0.8157   0.0079
  -9.250  -0.2714   0.11897   0.11611  -0.0168   0.8135   0.0080
  -9.000  -0.2598   0.11676   0.11392  -0.0199   0.8085   0.0080
  -8.750  -0.2551   0.11339   0.11054  -0.0178   0.8132   0.0081
  -8.500  -0.2447   0.11110   0.10825  -0.0202   0.8082   0.0081
  -8.250  -0.2351   0.10887   0.10603  -0.0223   0.8022   0.0081
  -8.000  -0.2275   0.10621   0.10337  -0.0226   0.8011   0.0082
  -7.750  -0.2202   0.10401   0.10114  -0.0234   0.7978   0.0082
  -7.500  -0.2112   0.10197   0.09915  -0.0256   0.7917   0.0082
  -7.250  -0.2039   0.09943   0.09660  -0.0260   0.7908   0.0082
  -7.000  -0.1942   0.09653   0.09370  -0.0262   0.7890   0.0082
  -6.750  -0.1796   0.09435   0.09146  -0.0301   0.7809   0.0082
  -5.750  -0.1213   0.08086   0.07818  -0.0377   0.6946   0.0087
  -5.500  -0.0710   0.07996   0.07704  -0.0628   0.6512   0.0089
  -5.250  -0.0470   0.07740   0.07445  -0.0678   0.6405   0.0091
  -5.000  -0.0212   0.07485   0.07186  -0.0730   0.6310   0.0095
  -4.750   0.0069   0.07260   0.06957  -0.0790   0.6217   0.0099
  -4.500   0.0337   0.07016   0.06708  -0.0834   0.6136   0.0103
  -4.250   0.0625   0.06782   0.06468  -0.0882   0.6064   0.0110
  -4.000   0.0990   0.06635   0.06315  -0.0947   0.5982   0.0117
  -3.750   0.1318   0.06434   0.06103  -0.0992   0.5924   0.0118
  -3.500   0.1581   0.06260   0.05923  -0.1024   0.5854   0.0118
  -3.250   0.1657   0.06013   0.05671  -0.1027   0.5793   0.0122
  -3.000   0.1643   0.05974   0.05633  -0.1004   0.5725   0.0124
  -2.750   0.1676   0.05872   0.05526  -0.0978   0.5674   0.0129
  -2.500   0.1520   0.05866   0.05517  -0.0911   0.5621   0.0130
  -2.250   0.1535   0.05798   0.05446  -0.0880   0.5566   0.0135
  -2.000   0.1395   0.05873   0.05512  -0.0828   0.5510   0.0139
  -1.750   0.1162   0.06080   0.05717  -0.0768   0.5445   0.0138
  -1.500   0.1216   0.06069   0.05697  -0.0748   0.5397   0.0149
  -1.250   0.0709   0.06624   0.06247  -0.0657   0.5326   0.0139
  -1.000   0.0401   0.07044   0.06661  -0.0592   0.5262   0.0137
  -0.750  -0.0191   0.07803   0.07415  -0.0484   0.5194   0.0130
  -0.500  -0.0378   0.08142   0.07751  -0.0428   0.5136   0.0130
  -0.250  -0.0398   0.08299   0.07903  -0.0392   0.5094   0.0134
   0.000  -0.0353   0.08396   0.07996  -0.0362   0.5054   0.0143
   0.250  -0.0200   0.08433   0.08029  -0.0342   0.5011   0.0160
   0.500   0.0045   0.08545   0.08132  -0.0325   0.4971   0.0168
   0.750   0.0036   0.08746   0.08325  -0.0284   0.4932   0.0168
   1.000  -0.0231   0.09137   0.08719  -0.0212   0.4879   0.0172
   1.250  -0.0484   0.09657   0.09237  -0.0136   0.4830   0.0172
   1.500  -0.0812   0.10357   0.09933  -0.0045   0.4785   0.0170
   1.750  -0.1081   0.10961   0.10541   0.0039   0.4731   0.0170
   2.000  -0.1338   0.11571   0.11149   0.0124   0.4684   0.0169
   2.250  -0.1741   0.12421   0.11997   0.0229   0.4640   0.0168
   2.500  -0.2031   0.13095   0.12677   0.0324   0.4588   0.0168
   2.750  -0.2103   0.13505   0.13086   0.0395   0.4550   0.0168
  13.250   1.6261   0.04381   0.03767  -0.0527   0.0048   0.8268
  13.500   1.6101   0.05012   0.04411  -0.0570   0.0045   0.8088
  13.750   1.5978   0.05510   0.04929  -0.0563   0.0044   0.8119
  14.000   1.5929   0.05942   0.05375  -0.0573   0.0043   0.8113
  14.250   1.5852   0.06411   0.05859  -0.0582   0.0042   0.8110
  14.500   1.5766   0.06885   0.06348  -0.0587   0.0040   0.8119
  14.750   1.5661   0.07368   0.06847  -0.0583   0.0039   0.8164
  15.000   1.5568   0.07905   0.07397  -0.0604   0.0039   0.8130
  15.250   1.5466   0.08416   0.07923  -0.0608   0.0038   0.8161
  15.500   1.5372   0.08938   0.08460  -0.0620   0.0038   0.8168
  15.750   1.5282   0.09510   0.09046  -0.0648   0.0037   0.8125
  16.000   1.5188   0.10060   0.09612  -0.0660   0.0037   0.8136
  16.250   1.5107   0.10625   0.10191  -0.0682   0.0036   0.8129
  16.500   1.5016   0.11202   0.10784  -0.0698   0.0036   0.8140
  16.750   1.4930   0.11789   0.11388  -0.0719   0.0036   0.8143
  17.000   1.4853   0.12385   0.11998  -0.0747   0.0035   0.8135
  17.250   1.4768   0.12997   0.12628  -0.0773   0.0035   0.8140
  17.500   1.4690   0.13616   0.13262  -0.0804   0.0034   0.8136
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