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EH 2.0/12 (eh2012-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EH 2.0/12 (eh2012-il)
Reynolds number: 50,000
Max Cl/Cd: 28.31 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh2012-il-50000-n5.txt
Download as CSV file: xf-eh2012-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 2.0/12                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5377   0.09703   0.09025  -0.0151   1.0000   0.0519
 -10.000  -0.5455   0.09057   0.08385  -0.0194   1.0000   0.0519
  -9.750  -0.5556   0.08386   0.07717  -0.0241   1.0000   0.0517
  -9.500  -0.5705   0.07792   0.07124  -0.0278   1.0000   0.0514
  -9.250  -0.5881   0.07291   0.06621  -0.0295   1.0000   0.0511
  -9.000  -0.6068   0.06857   0.06180  -0.0294   1.0000   0.0511
  -8.750  -0.6213   0.06412   0.05718  -0.0290   1.0000   0.0512
  -8.500  -0.6323   0.05974   0.05255  -0.0280   1.0000   0.0516
  -8.250  -0.6392   0.05544   0.04791  -0.0266   1.0000   0.0521
  -8.000  -0.6416   0.05132   0.04336  -0.0248   1.0000   0.0526
  -7.750  -0.6375   0.04769   0.03942  -0.0231   1.0000   0.0535
  -7.500  -0.6265   0.04517   0.03675  -0.0217   1.0000   0.0551
  -7.250  -0.6136   0.04315   0.03458  -0.0203   1.0000   0.0582
  -7.000  -0.6023   0.04049   0.03151  -0.0185   1.0000   0.0617
  -6.750  -0.5897   0.03747   0.02785  -0.0165   1.0000   0.0648
  -6.500  -0.5727   0.03558   0.02593  -0.0152   1.0000   0.0683
  -6.250  -0.5557   0.03398   0.02413  -0.0137   1.0000   0.0740
  -6.000  -0.5373   0.03201   0.02185  -0.0122   1.0000   0.0795
  -5.750  -0.5197   0.03075   0.02056  -0.0107   1.0000   0.0861
  -5.500  -0.5013   0.02936   0.01901  -0.0092   1.0000   0.0940
  -5.250  -0.4837   0.02827   0.01785  -0.0076   1.0000   0.1024
  -5.000  -0.4678   0.02733   0.01690  -0.0059   1.0000   0.1118
  -4.750  -0.4519   0.02647   0.01595  -0.0040   1.0000   0.1217
  -4.500  -0.4070   0.02533   0.01481  -0.0077   0.9832   0.1415
  -4.250  -0.3625   0.02427   0.01371  -0.0112   0.9659   0.1664
  -4.000  -0.3195   0.02319   0.01269  -0.0144   0.9483   0.1975
  -3.750  -0.2803   0.02207   0.01178  -0.0171   0.9299   0.2431
  -3.500  -0.2472   0.02074   0.01096  -0.0187   0.9112   0.3266
  -3.250  -0.2253   0.01923   0.01086  -0.0168   0.8917   0.5577
  -3.000  -0.1748   0.01958   0.01159  -0.0171   0.8769   0.7678
  -2.750  -0.1341   0.02009   0.01183  -0.0172   0.8583   0.8333
  -2.500  -0.0840   0.02061   0.01199  -0.0191   0.8405   0.8762
  -2.250  -0.0268   0.02097   0.01197  -0.0228   0.8225   0.9112
  -2.000   0.0555   0.02116   0.01174  -0.0314   0.8035   0.9545
  -1.750   0.1198   0.02083   0.01105  -0.0381   0.7826   0.9806
  -1.500   0.1598   0.02053   0.01048  -0.0408   0.7633   0.9917
  -1.250   0.1946   0.02031   0.01002  -0.0426   0.7448   1.0000
  -1.000   0.2140   0.02029   0.00983  -0.0415   0.7277   1.0000
  -0.750   0.2336   0.02030   0.00968  -0.0403   0.7117   1.0000
  -0.500   0.2535   0.02032   0.00956  -0.0392   0.6968   1.0000
  -0.250   0.2736   0.02037   0.00946  -0.0381   0.6826   1.0000
   0.000   0.2939   0.02042   0.00939  -0.0370   0.6692   1.0000
   0.250   0.3144   0.02049   0.00933  -0.0359   0.6565   1.0000
   0.500   0.3349   0.02059   0.00935  -0.0349   0.6434   1.0000
   0.750   0.3555   0.02072   0.00941  -0.0339   0.6308   1.0000
   1.000   0.3761   0.02086   0.00949  -0.0328   0.6188   1.0000
   1.250   0.3966   0.02102   0.00957  -0.0317   0.6076   1.0000
   1.500   0.4172   0.02118   0.00964  -0.0305   0.5972   1.0000
   1.750   0.4381   0.02141   0.00986  -0.0296   0.5855   1.0000
   2.000   0.4589   0.02165   0.01008  -0.0286   0.5746   1.0000
   2.250   0.4796   0.02187   0.01024  -0.0274   0.5647   1.0000
   2.500   0.5002   0.02214   0.01049  -0.0263   0.5544   1.0000
   2.750   0.5204   0.02245   0.01084  -0.0252   0.5439   1.0000
   3.000   0.5410   0.02273   0.01108  -0.0240   0.5347   1.0000
   3.250   0.5612   0.02305   0.01141  -0.0228   0.5249   1.0000
   3.500   0.5810   0.02344   0.01183  -0.0216   0.5149   1.0000
   3.750   0.6018   0.02372   0.01210  -0.0204   0.5065   1.0000
   4.000   0.6213   0.02416   0.01261  -0.0192   0.4964   1.0000
   4.250   0.6410   0.02459   0.01307  -0.0179   0.4871   1.0000
   4.750   0.6805   0.02547   0.01408  -0.0154   0.4690   1.0000
   5.000   0.7010   0.02586   0.01449  -0.0142   0.4608   1.0000
   5.250   0.7203   0.02638   0.01510  -0.0129   0.4515   1.0000
   5.500   0.7392   0.02694   0.01577  -0.0117   0.4424   1.0000
   5.750   0.7604   0.02731   0.01616  -0.0104   0.4345   1.0000
   6.000   0.7776   0.02803   0.01704  -0.0091   0.4248   1.0000
   6.250   0.7983   0.02847   0.01752  -0.0078   0.4168   1.0000
   6.500   0.8162   0.02914   0.01833  -0.0065   0.4075   1.0000
   6.750   0.8342   0.02982   0.01916  -0.0052   0.3986   1.0000
   7.000   0.8555   0.03022   0.01962  -0.0040   0.3906   1.0000
   7.250   0.8708   0.03115   0.02074  -0.0026   0.3808   1.0000
   7.500   0.8915   0.03162   0.02129  -0.0014   0.3727   1.0000
   7.750   0.9081   0.03243   0.02231   0.0000   0.3634   1.0000
   8.000   0.9241   0.03328   0.02334   0.0013   0.3540   1.0000
   8.250   0.9470   0.03357   0.02368   0.0024   0.3460   1.0000
   8.500   0.9582   0.03476   0.02512   0.0040   0.3356   1.0000
   8.750   0.9745   0.03556   0.02608   0.0054   0.3264   1.0000
   9.000   0.9953   0.03594   0.02659   0.0066   0.3174   1.0000
   9.250   1.0037   0.03727   0.02817   0.0083   0.3070   1.0000
   9.500   1.0180   0.03812   0.02918   0.0098   0.2974   1.0000
   9.750   1.0399   0.03826   0.02940   0.0111   0.2877   1.0000
  10.000   1.0424   0.03985   0.03125   0.0131   0.2769   1.0000
  10.250   1.0488   0.04103   0.03261   0.0150   0.2664   1.0000
  10.500   1.0597   0.04173   0.03344   0.0168   0.2556   1.0000
  10.750   1.0695   0.04226   0.03408   0.0187   0.2437   1.0000
  11.000   1.0625   0.04390   0.03588   0.0213   0.2331   1.0000
  11.250   1.0515   0.04608   0.03817   0.0233   0.2229   1.0000
  11.500   1.0451   0.04803   0.04018   0.0245   0.2112   1.0000
  11.750   1.0379   0.05030   0.04250   0.0250   0.1989   1.0000
  12.000   1.0298   0.05303   0.04526   0.0249   0.1863   1.0000
  12.250   1.0204   0.05623   0.04848   0.0243   0.1736   1.0000
  12.500   1.0114   0.05969   0.05195   0.0234   0.1610   1.0000
  12.750   0.9981   0.06417   0.05651   0.0218   0.1493   1.0000
  13.000   0.9856   0.06878   0.06118   0.0201   0.1379   1.0000
  13.250   0.9749   0.07323   0.06565   0.0185   0.1265   1.0000
  13.500   0.9654   0.07759   0.06998   0.0170   0.1152   1.0000
  13.750   0.9569   0.08186   0.07419   0.0155   0.1044   1.0000
  14.000   0.9502   0.08591   0.07811   0.0141   0.0945   1.0000
  14.250   0.9404   0.09099   0.08323   0.0121   0.0864   1.0000
  14.500   0.9328   0.09576   0.08798   0.0104   0.0794   1.0000
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