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EPPLER EA 6(-1)-012 AIRFOIL (ea61012-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER EA 6(-1)-012 AIRFOIL (ea61012-il)
Reynolds number: 50,000
Max Cl/Cd: 23.83 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ea61012-il-50000-n5.txt
Download as CSV file: xf-ea61012-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER EA 6(-1)-012 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.7454   0.09180   0.08372  -0.0190   1.0000   0.0896
 -11.500  -0.7797   0.08308   0.07495  -0.0246   1.0000   0.0892
 -11.250  -0.8117   0.07629   0.06805  -0.0279   1.0000   0.0889
 -11.000  -0.8415   0.07093   0.06253  -0.0292   1.0000   0.0889
 -10.750  -0.8674   0.06674   0.05814  -0.0285   1.0000   0.0890
 -10.500  -0.8870   0.06292   0.05403  -0.0270   1.0000   0.0895
 -10.250  -0.9000   0.05924   0.04999  -0.0255   1.0000   0.0901
 -10.000  -0.9005   0.05597   0.04645  -0.0244   1.0000   0.0909
  -9.750  -0.8917   0.05313   0.04343  -0.0235   1.0000   0.0918
  -9.500  -0.8813   0.05048   0.04058  -0.0227   1.0000   0.0927
  -9.250  -0.8692   0.04801   0.03786  -0.0218   1.0000   0.0937
  -9.000  -0.8550   0.04569   0.03532  -0.0209   1.0000   0.0949
  -8.750  -0.8393   0.04355   0.03295  -0.0201   1.0000   0.0966
  -8.500  -0.8231   0.04164   0.03077  -0.0193   1.0000   0.0993
  -8.250  -0.8064   0.03977   0.02854  -0.0183   1.0000   0.1021
  -8.000  -0.7863   0.03793   0.02649  -0.0177   1.0000   0.1043
  -7.750  -0.7627   0.03627   0.02477  -0.0174   1.0000   0.1063
  -7.500  -0.7388   0.03478   0.02321  -0.0170   1.0000   0.1083
  -7.250  -0.7143   0.03341   0.02175  -0.0166   1.0000   0.1108
  -7.000  -0.6890   0.03215   0.02038  -0.0161   1.0000   0.1136
  -6.750  -0.6633   0.03104   0.01910  -0.0157   1.0000   0.1170
  -6.500  -0.6392   0.02999   0.01811  -0.0151   1.0000   0.1215
  -6.250  -0.6170   0.02909   0.01726  -0.0143   1.0000   0.1274
  -6.000  -0.5946   0.02827   0.01634  -0.0134   1.0000   0.1333
  -5.750  -0.5753   0.02740   0.01555  -0.0122   1.0000   0.1384
  -5.500  -0.5592   0.02662   0.01482  -0.0105   1.0000   0.1448
  -5.250  -0.5464   0.02589   0.01414  -0.0083   1.0000   0.1523
  -5.000  -0.5374   0.02519   0.01351  -0.0056   1.0000   0.1616
  -4.750  -0.5307   0.02447   0.01292  -0.0027   1.0000   0.1750
  -4.500  -0.5247   0.02370   0.01232   0.0002   1.0000   0.1979
  -4.250  -0.5198   0.02273   0.01171   0.0031   1.0000   0.2371
  -4.000  -0.5133   0.02155   0.01116   0.0056   0.9989   0.3215
  -3.750  -0.4915   0.02065   0.01116   0.0064   0.9895   0.4582
  -3.500  -0.4644   0.02089   0.01184   0.0076   0.9818   0.5740
  -3.250  -0.4368   0.02125   0.01220   0.0083   0.9736   0.6340
  -3.000  -0.4118   0.02190   0.01284   0.0100   0.9655   0.6892
  -2.750  -0.3869   0.02283   0.01378   0.0125   0.9585   0.7382
  -2.500  -0.3614   0.02352   0.01445   0.0150   0.9521   0.7720
  -2.250  -0.3299   0.02385   0.01468   0.0154   0.9465   0.7950
  -2.000  -0.2971   0.02399   0.01470   0.0149   0.9412   0.8144
  -1.750  -0.2644   0.02404   0.01466   0.0143   0.9351   0.8275
  -1.500  -0.2266   0.02404   0.01456   0.0124   0.9303   0.8375
  -1.250  -0.1916   0.02398   0.01441   0.0107   0.9252   0.8481
  -1.000  -0.1584   0.02398   0.01435   0.0094   0.9190   0.8571
  -0.750  -0.1212   0.02397   0.01428   0.0074   0.9138   0.8659
  -0.500  -0.0836   0.02401   0.01428   0.0053   0.9089   0.8759
  -0.250  -0.0447   0.02410   0.01437   0.0031   0.9025   0.8857
   0.000   0.0000   0.02412   0.01437   0.0000   0.8958   0.8958
   0.250   0.0446   0.02410   0.01437  -0.0031   0.8857   0.9025
   0.500   0.0836   0.02401   0.01428  -0.0053   0.8759   0.9089
   0.750   0.1211   0.02397   0.01428  -0.0074   0.8660   0.9138
   1.000   0.1584   0.02398   0.01435  -0.0094   0.8571   0.9190
   1.250   0.1915   0.02398   0.01441  -0.0106   0.8481   0.9253
   1.500   0.2266   0.02403   0.01456  -0.0124   0.8375   0.9303
   1.750   0.2644   0.02404   0.01466  -0.0143   0.8275   0.9351
   2.000   0.2972   0.02398   0.01470  -0.0150   0.8146   0.9412
   2.250   0.3299   0.02385   0.01468  -0.0154   0.7950   0.9465
   2.500   0.3615   0.02351   0.01444  -0.0149   0.7719   0.9521
   2.750   0.3869   0.02282   0.01376  -0.0125   0.7380   0.9585
   3.000   0.4119   0.02190   0.01284  -0.0100   0.6896   0.9655
   3.250   0.4367   0.02125   0.01220  -0.0083   0.6343   0.9736
   3.500   0.4645   0.02089   0.01184  -0.0076   0.5751   0.9818
   3.750   0.4915   0.02064   0.01116  -0.0064   0.4587   0.9896
   4.000   0.5134   0.02154   0.01115  -0.0056   0.3226   0.9989
   4.250   0.5199   0.02271   0.01170  -0.0032   0.2381   1.0000
   4.500   0.5246   0.02370   0.01232  -0.0002   0.1981   1.0000
   4.750   0.5306   0.02446   0.01292   0.0027   0.1752   1.0000
   5.000   0.5374   0.02518   0.01350   0.0056   0.1618   1.0000
   5.250   0.5464   0.02589   0.01413   0.0083   0.1523   1.0000
   5.500   0.5592   0.02661   0.01482   0.0105   0.1449   1.0000
   5.750   0.5753   0.02740   0.01555   0.0122   0.1384   1.0000
   6.000   0.5946   0.02827   0.01634   0.0134   0.1333   1.0000
   6.250   0.6170   0.02909   0.01726   0.0143   0.1273   1.0000
   6.500   0.6392   0.02999   0.01810   0.0151   0.1215   1.0000
   6.750   0.6634   0.03103   0.01909   0.0157   0.1170   1.0000
   7.000   0.6890   0.03215   0.02038   0.0161   0.1136   1.0000
   7.250   0.7143   0.03341   0.02175   0.0166   0.1108   1.0000
   7.500   0.7388   0.03478   0.02321   0.0170   0.1083   1.0000
   7.750   0.7627   0.03627   0.02477   0.0174   0.1063   1.0000
   8.000   0.7863   0.03793   0.02649   0.0177   0.1043   1.0000
   8.250   0.8064   0.03977   0.02855   0.0183   0.1021   1.0000
   8.500   0.8231   0.04164   0.03077   0.0193   0.0993   1.0000
   8.750   0.8394   0.04354   0.03293   0.0201   0.0965   1.0000
   9.000   0.8551   0.04569   0.03531   0.0209   0.0949   1.0000
   9.250   0.8693   0.04801   0.03785   0.0218   0.0937   1.0000
   9.500   0.8815   0.05049   0.04058   0.0226   0.0927   1.0000
   9.750   0.8919   0.05313   0.04343   0.0235   0.0917   1.0000
  10.000   0.9009   0.05598   0.04645   0.0243   0.0909   1.0000
  10.250   0.9003   0.05924   0.04999   0.0255   0.0901   1.0000
  10.500   0.8875   0.06291   0.05403   0.0270   0.0895   1.0000
  10.750   0.8671   0.06677   0.05817   0.0284   0.0890   1.0000
  11.000   0.8410   0.07100   0.06260   0.0291   0.0888   1.0000
  11.250   0.8114   0.07636   0.06812   0.0278   0.0889   1.0000
  11.500   0.7796   0.08316   0.07504   0.0244   0.0892   1.0000
  11.750   0.7448   0.09203   0.08397   0.0188   0.0896   1.0000
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