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EPPLER 66 AIRFOIL (e66-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 66 AIRFOIL (e66-il)
Reynolds number: 50,000
Max Cl/Cd: 40.22 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e66-il-50000.txt
Download as CSV file: xf-e66-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 66 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3783   0.10411   0.09782  -0.0229   1.0000   0.2371
  -7.250  -0.3829   0.10217   0.09596  -0.0208   1.0000   0.2457
  -7.000  -0.4217   0.10339   0.09739  -0.0178   1.0000   0.2485
  -6.750  -0.4003   0.09846   0.09245  -0.0160   1.0000   0.2607
  -6.500  -0.4358   0.09896   0.09315  -0.0141   1.0000   0.2633
  -6.250  -0.4243   0.09519   0.08940  -0.0109   1.0000   0.2765
  -6.000  -0.4217   0.09226   0.08652  -0.0083   1.0000   0.2881
  -5.750  -0.4304   0.09005   0.08441  -0.0065   1.0000   0.2976
  -5.500  -0.4514   0.08902   0.08353  -0.0074   1.0000   0.3084
  -5.250  -0.4534   0.08650   0.08107  -0.0058   1.0000   0.3232
  -5.000  -0.4542   0.08386   0.07848  -0.0043   1.0000   0.3381
  -4.750  -0.4437   0.08030   0.07493   0.0000   1.0000   0.3479
  -4.500  -0.3651   0.04998   0.04274  -0.0603   1.0000   0.1319
  -4.250  -0.3382   0.04539   0.03786  -0.0626   1.0000   0.1290
  -4.000  -0.2987   0.04024   0.03170  -0.0680   1.0000   0.1313
  -3.750  -0.2734   0.03761   0.02900  -0.0686   1.0000   0.1379
  -3.500  -0.2373   0.03442   0.02496  -0.0712   1.0000   0.1467
  -3.250  -0.2092   0.03248   0.02273  -0.0718   1.0000   0.1618
  -3.000  -0.1834   0.03104   0.02123  -0.0719   1.0000   0.1826
  -2.750  -0.1566   0.02972   0.01980  -0.0720   1.0000   0.2140
  -2.500  -0.1316   0.02873   0.01886  -0.0718   1.0000   0.2591
  -2.250  -0.1071   0.02792   0.01821  -0.0715   1.0000   0.3142
  -2.000  -0.0827   0.02727   0.01769  -0.0710   1.0000   0.3829
  -1.750  -0.0603   0.02679   0.01755  -0.0699   1.0000   0.4623
  -1.500  -0.0402   0.02642   0.01755  -0.0682   1.0000   0.5561
  -1.250  -0.0258   0.02608   0.01765  -0.0649   1.0000   0.6620
  -1.000  -0.0224   0.02562   0.01767  -0.0589   1.0000   0.7803
  -0.750  -0.0159   0.02456   0.01675  -0.0559   1.0000   1.0000
  -0.500   0.0182   0.02516   0.01672  -0.0593   1.0000   1.0000
  -0.250   0.0439   0.02579   0.01694  -0.0606   1.0000   1.0000
   0.000   0.0674   0.02646   0.01730  -0.0613   1.0000   1.0000
   0.250   0.0897   0.02717   0.01772  -0.0618   1.0000   1.0000
   0.500   0.1112   0.02793   0.01825  -0.0622   1.0000   1.0000
   0.750   0.1320   0.02873   0.01886  -0.0625   1.0000   1.0000
   1.000   0.1522   0.02957   0.01954  -0.0627   1.0000   1.0000
   1.250   0.1719   0.03047   0.02028  -0.0630   1.0000   1.0000
   1.500   0.1912   0.03143   0.02111  -0.0632   1.0000   1.0000
   1.750   0.2281   0.03293   0.02249  -0.0668   0.9907   1.0000
   2.000   0.2752   0.03462   0.02404  -0.0720   0.9749   1.0000
   2.250   0.3203   0.03616   0.02549  -0.0767   0.9598   1.0000
   2.500   0.3593   0.03742   0.02669  -0.0801   0.9444   1.0000
   2.750   0.3948   0.03854   0.02777  -0.0829   0.9286   1.0000
   3.000   0.4302   0.03963   0.02886  -0.0854   0.9127   1.0000
   3.250   0.4657   0.04071   0.02994  -0.0879   0.8969   1.0000
   3.500   0.5017   0.04174   0.03101  -0.0903   0.8809   1.0000
   3.750   0.5393   0.04271   0.03202  -0.0928   0.8648   1.0000
   4.000   0.5781   0.04360   0.03296  -0.0952   0.8487   1.0000
   4.250   0.6171   0.04438   0.03385  -0.0974   0.8325   1.0000
   4.500   0.6417   0.04522   0.03478  -0.0977   0.8140   1.0000
   4.750   0.6747   0.04590   0.03557  -0.0988   0.7961   1.0000
   5.000   0.7133   0.04635   0.03619  -0.1004   0.7787   1.0000
   5.250   0.7578   0.04642   0.03644  -0.1023   0.7618   1.0000
   5.500   0.7818   0.04707   0.03723  -0.1018   0.7414   1.0000
   5.750   0.8201   0.04701   0.03740  -0.1024   0.7223   1.0000
   6.000   0.8720   0.04595   0.03661  -0.1038   0.7046   1.0000
   6.250   0.9018   0.04584   0.03671  -0.1030   0.6828   1.0000
   6.500   0.9598   0.04341   0.03467  -0.1035   0.6637   1.0000
   6.750   1.0443   0.03874   0.03046  -0.1057   0.6431   1.0000
   7.000   1.1161   0.03491   0.02705  -0.1070   0.6131   1.0000
   7.250   1.1805   0.03168   0.02402  -0.1076   0.5720   1.0000
   7.500   1.2107   0.03083   0.02323  -0.1051   0.5259   1.0000
   7.750   1.2330   0.03066   0.02293  -0.1020   0.4749   1.0000
   8.000   1.2484   0.03116   0.02317  -0.0984   0.4219   1.0000
   8.250   1.2612   0.03215   0.02376  -0.0948   0.3687   1.0000
   8.500   1.2675   0.03372   0.02508  -0.0908   0.3201   1.0000
   8.750   1.2752   0.03554   0.02660  -0.0873   0.2751   1.0000
   9.000   1.2838   0.03761   0.02841  -0.0842   0.2348   1.0000
   9.250   1.2933   0.03987   0.03044  -0.0814   0.1998   1.0000
   9.500   1.3095   0.04251   0.03272  -0.0797   0.1682   1.0000
   9.750   1.3211   0.04530   0.03570  -0.0773   0.1464   1.0000
  10.000   1.3456   0.04866   0.03885  -0.0770   0.1268   1.0000
  10.250   1.3611   0.05205   0.04260  -0.0752   0.1160   1.0000
  10.500   1.3676   0.05564   0.04663  -0.0725   0.1087   1.0000
  10.750   1.3920   0.06002   0.05095  -0.0726   0.1005   1.0000
  11.000   1.3850   0.06379   0.05535  -0.0686   0.0990   1.0000
  11.250   1.3736   0.06762   0.05973  -0.0646   0.0977   1.0000
  11.500   1.3572   0.07131   0.06381  -0.0604   0.0969   1.0000
  11.750   1.3378   0.07519   0.06804  -0.0567   0.0964   1.0000
  12.000   1.3157   0.07942   0.07258  -0.0538   0.0964   1.0000
  12.250   1.2913   0.08412   0.07751  -0.0518   0.0968   1.0000
  12.500   1.2658   0.08939   0.08302  -0.0508   0.0975   1.0000
  12.750   1.2402   0.09525   0.08908  -0.0510   0.0984   1.0000
  13.000   1.2157   0.10171   0.09570  -0.0523   0.0992   1.0000
  13.250   1.1938   0.10869   0.10280  -0.0545   0.1001   1.0000
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