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EPPLER 67 AIRFOIL (e67-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 67 AIRFOIL (e67-il)
Reynolds number: 50,000
Max Cl/Cd: 36.94 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e67-il-50000-n5.txt
Download as CSV file: xf-e67-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 67 AIRFOIL                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3932   0.10343   0.09650  -0.0462   1.0000   0.0493
  -9.250  -0.4001   0.10008   0.09323  -0.0460   1.0000   0.0489
  -9.000  -0.4090   0.09667   0.08993  -0.0457   1.0000   0.0487
  -8.750  -0.4199   0.09329   0.08666  -0.0453   1.0000   0.0483
  -8.500  -0.4334   0.08990   0.08339  -0.0448   1.0000   0.0480
  -8.250  -0.4500   0.08656   0.08017  -0.0440   1.0000   0.0476
  -8.000  -0.4703   0.08322   0.07696  -0.0431   1.0000   0.0471
  -7.750  -0.4905   0.07865   0.07253  -0.0441   1.0000   0.0466
  -7.500  -0.5095   0.07283   0.06673  -0.0469   1.0000   0.0459
  -7.250  -0.5254   0.06735   0.06118  -0.0488   1.0000   0.0454
  -7.000  -0.5359   0.06174   0.05538  -0.0509   1.0000   0.0451
  -6.750  -0.5387   0.05632   0.04964  -0.0528   1.0000   0.0451
  -6.500  -0.5337   0.05129   0.04418  -0.0546   1.0000   0.0456
  -6.250  -0.5221   0.04692   0.03931  -0.0560   1.0000   0.0467
  -6.000  -0.4999   0.04277   0.03444  -0.0584   0.9982   0.0495
  -5.750  -0.4689   0.03928   0.03032  -0.0615   0.9943   0.0535
  -5.500  -0.4387   0.03712   0.02787  -0.0634   0.9900   0.0575
  -5.250  -0.4056   0.03478   0.02486  -0.0652   0.9860   0.0639
  -5.000  -0.3745   0.03337   0.02339  -0.0669   0.9818   0.0728
  -4.750  -0.3440   0.03197   0.02180  -0.0682   0.9770   0.0841
  -4.500  -0.3110   0.03080   0.02042  -0.0698   0.9727   0.0999
  -4.250  -0.2803   0.02980   0.01927  -0.0708   0.9677   0.1198
  -4.000  -0.2491   0.02899   0.01842  -0.0722   0.9625   0.1456
  -3.750  -0.2148   0.02830   0.01776  -0.0741   0.9582   0.1785
  -3.500  -0.1870   0.02768   0.01717  -0.0748   0.9520   0.2144
  -3.250  -0.1529   0.02721   0.01675  -0.0766   0.9470   0.2629
  -3.000  -0.1230   0.02681   0.01649  -0.0776   0.9412   0.3146
  -2.750  -0.0921   0.02652   0.01634  -0.0787   0.9353   0.3740
  -2.500  -0.0593   0.02633   0.01626  -0.0798   0.9302   0.4399
  -2.250  -0.0339   0.02619   0.01626  -0.0795   0.9229   0.5005
  -2.000  -0.0021   0.02614   0.01634  -0.0801   0.9179   0.5659
  -1.750   0.0192   0.02610   0.01640  -0.0787   0.9099   0.6223
  -1.500   0.0474   0.02609   0.01645  -0.0782   0.9043   0.6825
  -1.250   0.0657   0.02608   0.01651  -0.0759   0.8961   0.7368
  -1.000   0.0908   0.02603   0.01650  -0.0746   0.8901   0.7983
  -0.750   0.1090   0.02595   0.01646  -0.0722   0.8816   0.8653
  -0.500   0.1569   0.02575   0.01614  -0.0761   0.8759   1.0000
  -0.250   0.1849   0.02598   0.01612  -0.0772   0.8672   1.0000
   0.000   0.2230   0.02618   0.01606  -0.0797   0.8615   1.0000
   0.250   0.2488   0.02647   0.01617  -0.0801   0.8523   1.0000
   0.750   0.3110   0.02697   0.01636  -0.0823   0.8370   1.0000
   1.000   0.3499   0.02710   0.01635  -0.0845   0.8319   1.0000
   1.250   0.3724   0.02747   0.01663  -0.0841   0.8215   1.0000
   1.500   0.4028   0.02771   0.01679  -0.0849   0.8137   1.0000
   1.750   0.4338   0.02792   0.01694  -0.0857   0.8058   1.0000
   2.000   0.4596   0.02825   0.01722  -0.0857   0.7963   1.0000
   2.250   0.4959   0.02829   0.01724  -0.0871   0.7900   1.0000
   2.500   0.5190   0.02867   0.01760  -0.0866   0.7793   1.0000
   2.750   0.5512   0.02876   0.01769  -0.0873   0.7716   1.0000
   3.000   0.5806   0.02892   0.01786  -0.0876   0.7626   1.0000
   3.250   0.6052   0.02922   0.01821  -0.0872   0.7520   1.0000
   3.500   0.6449   0.02898   0.01801  -0.0887   0.7461   1.0000
   3.750   0.6671   0.02933   0.01841  -0.0879   0.7342   1.0000
   4.000   0.6922   0.02957   0.01875  -0.0874   0.7231   1.0000
   4.250   0.7290   0.02934   0.01860  -0.0884   0.7153   1.0000
   4.500   0.7572   0.02941   0.01876  -0.0881   0.7043   1.0000
   4.750   0.7819   0.02959   0.01904  -0.0875   0.6919   1.0000
   5.000   0.8092   0.02965   0.01924  -0.0870   0.6798   1.0000
   5.250   0.8390   0.02957   0.01928  -0.0868   0.6678   1.0000
   5.500   0.8710   0.02937   0.01921  -0.0868   0.6556   1.0000
   5.750   0.9018   0.02918   0.01917  -0.0866   0.6420   1.0000
   6.000   0.9287   0.02914   0.01930  -0.0858   0.6267   1.0000
   6.250   0.9542   0.02912   0.01943  -0.0849   0.6100   1.0000
   6.500   0.9810   0.02903   0.01948  -0.0840   0.5923   1.0000
   6.750   1.0116   0.02877   0.01938  -0.0835   0.5735   1.0000
   7.000   1.0309   0.02897   0.01971  -0.0816   0.5518   1.0000
   7.250   1.0579   0.02886   0.01969  -0.0806   0.5290   1.0000
   7.500   1.0741   0.02922   0.02015  -0.0783   0.5036   1.0000
   7.750   1.0918   0.02956   0.02054  -0.0762   0.4766   1.0000
   8.000   1.1079   0.03001   0.02105  -0.0740   0.4477   1.0000
   8.250   1.1216   0.03061   0.02165  -0.0715   0.4176   1.0000
   8.500   1.1329   0.03138   0.02238  -0.0689   0.3863   1.0000
   8.750   1.1420   0.03234   0.02328  -0.0662   0.3551   1.0000
   9.000   1.1483   0.03354   0.02441  -0.0635   0.3238   1.0000
   9.250   1.1533   0.03491   0.02572  -0.0608   0.2936   1.0000
   9.500   1.1571   0.03647   0.02721  -0.0582   0.2648   1.0000
   9.750   1.1598   0.03822   0.02886  -0.0557   0.2379   1.0000
  10.000   1.1620   0.04012   0.03074  -0.0535   0.2134   1.0000
  10.250   1.1640   0.04217   0.03277  -0.0515   0.1899   1.0000
  10.500   1.1651   0.04439   0.03491  -0.0496   0.1704   1.0000
  10.750   1.1667   0.04673   0.03725  -0.0479   0.1506   1.0000
  11.000   1.1680   0.04919   0.03970  -0.0464   0.1341   1.0000
  11.250   1.1686   0.05179   0.04230  -0.0451   0.1193   1.0000
  11.500   1.1700   0.05447   0.04501  -0.0440   0.1064   1.0000
  11.750   1.1712   0.05725   0.04785  -0.0430   0.0951   1.0000
  12.000   1.1730   0.06010   0.05074  -0.0421   0.0858   1.0000
  12.250   1.1740   0.06302   0.05369  -0.0414   0.0780   1.0000
  12.500   1.1780   0.06596   0.05685  -0.0406   0.0704   1.0000
  12.750   1.1802   0.06891   0.05982  -0.0401   0.0652   1.0000
  13.000   1.1843   0.07212   0.06336  -0.0396   0.0597   1.0000
  13.250   1.1859   0.07535   0.06672  -0.0394   0.0557   1.0000
  13.500   1.1928   0.07833   0.06973  -0.0389   0.0526   1.0000
  13.750   1.1926   0.08250   0.07433  -0.0388   0.0502   1.0000
  14.000   1.1877   0.08704   0.07918  -0.0394   0.0481   1.0000
  14.250   1.1810   0.09176   0.08414  -0.0404   0.0464   1.0000
  14.500   1.1739   0.09651   0.08906  -0.0418   0.0448   1.0000
  14.750   1.1704   0.10074   0.09336  -0.0430   0.0432   1.0000
  15.000   1.1615   0.10627   0.09904  -0.0451   0.0422   1.0000
  15.250   1.1449   0.11345   0.10651  -0.0486   0.0420   1.0000
  15.500   1.1269   0.12133   0.11463  -0.0529   0.0419   1.0000
  15.750   1.1075   0.13011   0.12363  -0.0582   0.0420   1.0000
  16.000   1.0879   0.13969   0.13338  -0.0642   0.0422   1.0000
  16.250   1.0686   0.15005   0.14386  -0.0708   0.0424   1.0000
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