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EPPLER 582 AIRFOIL (e582-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 582 AIRFOIL (e582-il)
Reynolds number: 100,000
Max Cl/Cd: 45.41 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e582-il-100000-n5.txt
Download as CSV file: xf-e582-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 582 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1668   0.08086   0.07599  -0.1043   0.9312   0.0239
  -9.000  -0.1588   0.07722   0.07234  -0.1070   0.9235   0.0235
  -8.750  -0.1516   0.07181   0.06691  -0.1129   0.9173   0.0230
  -8.500  -0.1534   0.06661   0.06166  -0.1178   0.9077   0.0225
  -8.250  -0.1578   0.06145   0.05637  -0.1219   0.8995   0.0219
  -8.000  -0.1695   0.05762   0.05241  -0.1223   0.8886   0.0215
  -7.750  -0.1767   0.05367   0.04824  -0.1221   0.8798   0.0210
  -7.500  -0.1805   0.04940   0.04365  -0.1217   0.8723   0.0203
  -7.250  -0.1876   0.04508   0.03889  -0.1195   0.8639   0.0196
  -7.000  -0.1849   0.04104   0.03421  -0.1176   0.8575   0.0191
  -6.750  -0.1729   0.03831   0.03109  -0.1166   0.8526   0.0190
  -6.500  -0.1637   0.03616   0.02860  -0.1145   0.8458   0.0190
  -6.250  -0.1446   0.03361   0.02557  -0.1139   0.8417   0.0191
  -6.000  -0.1235   0.03143   0.02304  -0.1134   0.8380   0.0193
  -5.750  -0.1090   0.03004   0.02142  -0.1114   0.8317   0.0196
  -5.500  -0.0848   0.02849   0.01961  -0.1111   0.8278   0.0202
  -5.250  -0.0564   0.02706   0.01794  -0.1114   0.8250   0.0213
  -5.000  -0.0373   0.02615   0.01683  -0.1099   0.8198   0.0229
  -4.750  -0.0160   0.02524   0.01578  -0.1088   0.8150   0.0251
  -4.500   0.0104   0.02428   0.01473  -0.1087   0.8117   0.0277
  -4.250   0.0387   0.02323   0.01352  -0.1087   0.8091   0.0302
  -4.000   0.0523   0.02283   0.01317  -0.1064   0.8029   0.0343
  -3.750   0.0740   0.02220   0.01249  -0.1055   0.7986   0.0417
  -3.500   0.1004   0.02147   0.01171  -0.1053   0.7955   0.0574
  -3.250   0.1269   0.02061   0.01107  -0.1053   0.7928   0.0985
  -3.000   0.1365   0.02022   0.01109  -0.1025   0.7861   0.1716
  -2.750   0.1530   0.01902   0.01083  -0.1013   0.7821   0.3840
  -2.500   0.1572   0.01891   0.01206  -0.0935   0.7791   0.6888
  -2.250   0.1714   0.01941   0.01237  -0.0911   0.7735   0.7680
  -2.000   0.1856   0.01992   0.01274  -0.0876   0.7685   0.8016
  -1.750   0.2051   0.02024   0.01292  -0.0847   0.7652   0.8266
  -1.500   0.2281   0.02042   0.01293  -0.0824   0.7628   0.8487
  -1.250   0.2267   0.02094   0.01344  -0.0760   0.7554   0.8700
  -1.000   0.2464   0.02113   0.01353  -0.0727   0.7518   0.8981
  -0.750   0.2825   0.02111   0.01333  -0.0734   0.7495   0.9168
  -0.500   0.3189   0.02094   0.01297  -0.0751   0.7474   0.9211
  -0.250   0.3241   0.02128   0.01329  -0.0715   0.7395   0.9275
   0.000   0.3484   0.02120   0.01309  -0.0711   0.7358   0.9317
   0.250   0.3822   0.02105   0.01279  -0.0725   0.7333   0.9341
   0.500   0.3972   0.02131   0.01301  -0.0707   0.7270   0.9381
   0.750   0.4195   0.02136   0.01299  -0.0702   0.7221   0.9414
   1.000   0.4499   0.02125   0.01278  -0.0709   0.7191   0.9437
   1.250   0.4844   0.02107   0.01249  -0.0723   0.7168   0.9454
   1.500   0.4864   0.02159   0.01304  -0.0685   0.7080   0.9503
   1.750   0.5183   0.02150   0.01289  -0.0695   0.7046   0.9520
   2.000   0.5546   0.02133   0.01264  -0.0713   0.7022   0.9530
   2.250   0.5555   0.02185   0.01320  -0.0673   0.6934   0.9588
   2.500   0.5866   0.02178   0.01310  -0.0682   0.6896   0.9605
   2.750   0.6247   0.02157   0.01284  -0.0702   0.6870   0.9612
   3.000   0.6333   0.02212   0.01344  -0.0677   0.6782   0.9656
   3.250   0.6662   0.02202   0.01334  -0.0689   0.6742   0.9676
   3.500   0.7056   0.02175   0.01304  -0.0711   0.6715   0.9686
   3.750   0.7119   0.02237   0.01374  -0.0684   0.6619   0.9741
   4.000   0.7486   0.02218   0.01354  -0.0701   0.6582   0.9753
   4.250   0.7686   0.02248   0.01392  -0.0695   0.6511   0.9796
   4.500   0.7954   0.02254   0.01402  -0.0698   0.6451   0.9834
   4.750   0.8374   0.02216   0.01365  -0.0723   0.6417   0.9843
   5.000   0.8439   0.02273   0.01431  -0.0697   0.6317   1.0000
   5.250   0.8802   0.02236   0.01398  -0.0711   0.6274   1.0000
   5.500   0.8752   0.02295   0.01464  -0.0663   0.6173   1.0000
   5.750   0.9123   0.02256   0.01428  -0.0678   0.6125   1.0000
   6.250   0.9565   0.02270   0.01456  -0.0666   0.5971   1.0000
   6.500   0.9641   0.02336   0.01531  -0.0642   0.5863   1.0000
   6.750   0.9920   0.02329   0.01530  -0.0644   0.5784   1.0000
   7.000   1.0147   0.02343   0.01553  -0.0640   0.5689   1.0000
   7.250   1.0305   0.02390   0.01608  -0.0628   0.5579   1.0000
   7.500   1.0562   0.02393   0.01619  -0.0628   0.5479   1.0000
   7.750   1.0839   0.02387   0.01620  -0.0630   0.5372   1.0000
   8.000   1.0992   0.02439   0.01681  -0.0617   0.5240   1.0000
   8.250   1.1172   0.02481   0.01731  -0.0608   0.5105   1.0000
   8.750   1.1554   0.02560   0.01823  -0.0593   0.4813   1.0000
   9.000   1.1735   0.02607   0.01873  -0.0584   0.4654   1.0000
   9.250   1.1912   0.02657   0.01926  -0.0574   0.4486   1.0000
   9.500   1.2066   0.02722   0.01992  -0.0563   0.4309   1.0000
   9.750   1.2183   0.02812   0.02087  -0.0549   0.4124   1.0000
  10.000   1.2298   0.02906   0.02181  -0.0535   0.3933   1.0000
  10.250   1.2409   0.03006   0.02280  -0.0521   0.3743   1.0000
  10.500   1.2500   0.03122   0.02394  -0.0506   0.3551   1.0000
  10.750   1.2572   0.03256   0.02529  -0.0491   0.3360   1.0000
  11.000   1.2638   0.03398   0.02672  -0.0476   0.3173   1.0000
  11.250   1.2694   0.03551   0.02824  -0.0461   0.2991   1.0000
  11.500   1.2741   0.03716   0.02988  -0.0447   0.2813   1.0000
  11.750   1.2781   0.03894   0.03168  -0.0434   0.2636   1.0000
  12.000   1.2812   0.04085   0.03360  -0.0421   0.2463   1.0000
  12.250   1.2836   0.04288   0.03563  -0.0409   0.2295   1.0000
  12.500   1.2852   0.04504   0.03782  -0.0398   0.2133   1.0000
  12.750   1.2864   0.04733   0.04012  -0.0388   0.1976   1.0000
  13.000   1.2870   0.04976   0.04256  -0.0380   0.1826   1.0000
  13.250   1.2873   0.05232   0.04513  -0.0373   0.1682   1.0000
  13.500   1.2872   0.05500   0.04784  -0.0367   0.1544   1.0000
  13.750   1.2866   0.05784   0.05072  -0.0362   0.1411   1.0000
  14.000   1.2858   0.06078   0.05371  -0.0359   0.1287   1.0000
  14.250   1.2845   0.06388   0.05686  -0.0357   0.1171   1.0000
  14.500   1.2825   0.06715   0.06018  -0.0357   0.1064   1.0000
  14.750   1.2793   0.07067   0.06373  -0.0358   0.0969   1.0000
  15.000   1.2756   0.07438   0.06750  -0.0361   0.0879   1.0000
  15.250   1.2734   0.07798   0.07121  -0.0365   0.0796   1.0000
  15.500   1.2686   0.08200   0.07528  -0.0371   0.0728   1.0000
  15.750   1.2643   0.08608   0.07946  -0.0379   0.0661   1.0000
  16.000   1.2597   0.09028   0.08374  -0.0388   0.0605   1.0000
  16.250   1.2544   0.09470   0.08825  -0.0399   0.0554   1.0000
  16.500   1.2488   0.09920   0.09284  -0.0412   0.0510   1.0000
  16.750   1.2443   0.10366   0.09743  -0.0426   0.0468   1.0000
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