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EH 2.0/12 (eh2012-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EH 2.0/12 (eh2012-il)
Reynolds number: 500,000
Max Cl/Cd: 89.28 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eh2012-il-500000.txt
Download as CSV file: xf-eh2012-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7155   0.06225   0.05995  -0.0301   1.0000   0.0142
 -11.250  -0.7518   0.05306   0.05056  -0.0373   1.0000   0.0140
 -11.000  -0.7808   0.04775   0.04505  -0.0383   1.0000   0.0139
 -10.750  -0.8128   0.04314   0.04018  -0.0361   1.0000   0.0137
 -10.500  -0.8375   0.03956   0.03633  -0.0318   1.0000   0.0136
 -10.250  -0.8515   0.03578   0.03219  -0.0282   1.0000   0.0136
 -10.000  -0.8558   0.03243   0.02847  -0.0252   1.0000   0.0137
  -9.750  -0.8519   0.02970   0.02540  -0.0227   1.0000   0.0138
  -9.500  -0.8424   0.02747   0.02287  -0.0205   1.0000   0.0141
  -9.250  -0.8295   0.02556   0.02069  -0.0187   1.0000   0.0143
  -9.000  -0.8135   0.02404   0.01894  -0.0171   1.0000   0.0146
  -8.750  -0.7955   0.02280   0.01750  -0.0156   1.0000   0.0148
  -8.500  -0.7781   0.02131   0.01581  -0.0141   1.0000   0.0151
  -8.250  -0.7632   0.01923   0.01354  -0.0122   1.0000   0.0157
  -8.000  -0.7441   0.01826   0.01251  -0.0108   1.0000   0.0162
  -7.750  -0.7241   0.01760   0.01181  -0.0095   1.0000   0.0170
  -7.500  -0.7040   0.01705   0.01122  -0.0082   1.0000   0.0179
  -7.250  -0.6852   0.01639   0.01048  -0.0065   1.0000   0.0188
  -7.000  -0.6552   0.01583   0.00983  -0.0071   0.9952   0.0196
  -6.750  -0.6203   0.01438   0.00833  -0.0091   0.9842   0.0217
  -6.500  -0.5821   0.01379   0.00770  -0.0113   0.9696   0.0241
  -6.250  -0.5472   0.01303   0.00685  -0.0129   0.9469   0.0268
  -6.000  -0.5172   0.01258   0.00636  -0.0132   0.9173   0.0308
  -5.750  -0.4941   0.01217   0.00584  -0.0120   0.8861   0.0354
  -5.500  -0.4708   0.01195   0.00554  -0.0109   0.8573   0.0406
  -5.250  -0.4481   0.01160   0.00510  -0.0097   0.8316   0.0470
  -5.000  -0.4232   0.01151   0.00487  -0.0090   0.8078   0.0528
  -4.750  -0.3994   0.01117   0.00450  -0.0081   0.7859   0.0614
  -4.500  -0.3747   0.01095   0.00419  -0.0073   0.7656   0.0694
  -4.250  -0.3491   0.01082   0.00397  -0.0068   0.7469   0.0777
  -4.000  -0.3240   0.01057   0.00370  -0.0062   0.7292   0.0892
  -3.750  -0.2987   0.01036   0.00346  -0.0056   0.7123   0.1019
  -3.500  -0.2731   0.01016   0.00325  -0.0051   0.6964   0.1171
  -3.250  -0.2476   0.00995   0.00304  -0.0046   0.6815   0.1368
  -3.000  -0.2222   0.00972   0.00284  -0.0041   0.6670   0.1637
  -2.750  -0.1974   0.00943   0.00266  -0.0036   0.6534   0.2041
  -2.500  -0.1734   0.00905   0.00248  -0.0030   0.6405   0.2693
  -2.250  -0.1522   0.00840   0.00225  -0.0019   0.6280   0.3937
  -2.000  -0.1359   0.00748   0.00207   0.0001   0.6164   0.5928
  -1.750  -0.1151   0.00710   0.00205   0.0018   0.6050   0.7042
  -1.500  -0.0908   0.00699   0.00206   0.0028   0.5940   0.7621
  -1.250  -0.0654   0.00698   0.00207   0.0037   0.5830   0.7980
  -1.000  -0.0391   0.00699   0.00209   0.0043   0.5720   0.8230
  -0.750  -0.0128   0.00703   0.00211   0.0049   0.5618   0.8432
  -0.500   0.0137   0.00710   0.00212   0.0055   0.5519   0.8594
  -0.250   0.0403   0.00715   0.00216   0.0061   0.5415   0.8740
   0.000   0.0669   0.00723   0.00219   0.0066   0.5319   0.8869
   0.500   0.1184   0.00745   0.00235   0.0084   0.5131   0.9159
   0.750   0.1442   0.00760   0.00246   0.0093   0.5042   0.9291
   1.000   0.1709   0.00778   0.00260   0.0100   0.4950   0.9420
   1.250   0.2060   0.00797   0.00274   0.0089   0.4854   0.9488
   1.500   0.2324   0.00808   0.00277   0.0093   0.4772   0.9557
   1.750   0.2686   0.00816   0.00282   0.0076   0.4675   0.9577
   2.000   0.3045   0.00826   0.00287   0.0059   0.4585   0.9599
   2.250   0.3402   0.00838   0.00292   0.0042   0.4495   0.9624
   2.500   0.3750   0.00846   0.00298   0.0027   0.4403   0.9654
   2.750   0.4045   0.00858   0.00303   0.0023   0.4323   0.9702
   3.000   0.4424   0.00865   0.00309   0.0001   0.4229   0.9716
   3.250   0.4793   0.00875   0.00315  -0.0019   0.4142   0.9733
   3.500   0.5149   0.00886   0.00321  -0.0037   0.4054   0.9756
   3.750   0.5490   0.00894   0.00330  -0.0051   0.3968   0.9786
   4.000   0.5790   0.00909   0.00339  -0.0057   0.3888   0.9829
   4.250   0.6160   0.00915   0.00346  -0.0077   0.3796   0.9844
   4.500   0.6519   0.00925   0.00355  -0.0096   0.3715   0.9865
   4.750   0.6867   0.00936   0.00364  -0.0113   0.3627   0.9890
   5.000   0.7205   0.00946   0.00375  -0.0127   0.3542   0.9918
   5.500   0.7894   0.00968   0.00398  -0.0159   0.3366   0.9964
   5.750   0.8241   0.00981   0.00410  -0.0176   0.3279   0.9988
   6.000   0.8536   0.00994   0.00424  -0.0183   0.3194   1.0000
   6.250   0.8750   0.01007   0.00440  -0.0172   0.3117   1.0000
   6.500   0.8959   0.01024   0.00456  -0.0161   0.3038   1.0000
   6.750   0.9171   0.01038   0.00474  -0.0149   0.2957   1.0000
   7.250   0.9582   0.01075   0.00514  -0.0125   0.2782   1.0000
   7.500   0.9785   0.01096   0.00535  -0.0112   0.2673   1.0000
   7.750   0.9983   0.01119   0.00556  -0.0099   0.2540   1.0000
   8.000   1.0180   0.01145   0.00580  -0.0086   0.2393   1.0000
   8.250   1.0374   0.01175   0.00608  -0.0072   0.2246   1.0000
   8.500   1.0568   0.01208   0.00639  -0.0059   0.2111   1.0000
   8.750   1.0759   0.01245   0.00672  -0.0045   0.1961   1.0000
   9.000   1.0945   0.01287   0.00710  -0.0031   0.1794   1.0000
   9.250   1.1122   0.01338   0.00754  -0.0016   0.1620   1.0000
   9.500   1.1291   0.01395   0.00804  -0.0001   0.1407   1.0000
   9.750   1.1436   0.01471   0.00868   0.0017   0.1152   1.0000
  10.000   1.1533   0.01582   0.00957   0.0041   0.0814   1.0000
  10.250   1.1557   0.01740   0.01086   0.0073   0.0415   1.0000
  10.500   1.1603   0.01875   0.01209   0.0102   0.0256   1.0000
  10.750   1.1690   0.01974   0.01313   0.0126   0.0211   1.0000
  11.000   1.1715   0.02082   0.01425   0.0159   0.0187   1.0000
  11.250   1.1729   0.02190   0.01542   0.0191   0.0174   1.0000
  11.500   1.1778   0.02296   0.01657   0.0213   0.0165   1.0000
  11.750   1.1801   0.02434   0.01805   0.0233   0.0154   1.0000
  12.000   1.1803   0.02609   0.01988   0.0247   0.0145   1.0000
  12.250   1.1765   0.02844   0.02232   0.0257   0.0140   1.0000
  12.500   1.1650   0.03183   0.02585   0.0261   0.0134   1.0000
  12.750   1.1652   0.03436   0.02848   0.0260   0.0132   1.0000
  13.000   1.1640   0.03715   0.03138   0.0257   0.0130   1.0000
  13.250   1.1642   0.03991   0.03424   0.0253   0.0124   1.0000
  13.500   1.1605   0.04315   0.03758   0.0247   0.0122   1.0000
  13.750   1.1556   0.04662   0.04115   0.0239   0.0119   1.0000
  14.000   1.1499   0.05021   0.04483   0.0230   0.0118   1.0000
  14.250   1.1449   0.05381   0.04851   0.0221   0.0114   1.0000
  14.500   1.1387   0.05757   0.05236   0.0210   0.0112   1.0000
  14.750   1.1329   0.06143   0.05629   0.0198   0.0108   1.0000
  15.000   1.1268   0.06539   0.06034   0.0186   0.0108   1.0000
  15.250   1.1223   0.06923   0.06426   0.0173   0.0107   1.0000
  15.500   1.1128   0.07376   0.06884   0.0158   0.0102   1.0000
  15.750   1.1123   0.07721   0.07239   0.0146   0.0103   1.0000
  16.000   1.1042   0.08125   0.07649   0.0138   0.0099   1.0000
  16.250   1.1020   0.08480   0.08012   0.0129   0.0098   1.0000
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