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EPPLER 580 AIRFOIL (e580-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 580 AIRFOIL (e580-il)
Reynolds number: 100,000
Max Cl/Cd: 52.13 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e580-il-100000.txt
Download as CSV file: xf-e580-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 580 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3404   0.12018   0.11567  -0.0388   1.0000   0.1221
  -9.750  -0.3688   0.11841   0.11404  -0.0395   1.0000   0.1266
  -9.500  -0.4115   0.11672   0.11251  -0.0409   1.0000   0.1276
  -9.250  -0.3780   0.11337   0.10914  -0.0359   1.0000   0.1311
  -9.000  -0.3771   0.11184   0.10765  -0.0333   1.0000   0.1345
  -8.750  -0.3903   0.11013   0.10603  -0.0319   1.0000   0.1386
  -8.500  -0.4462   0.10836   0.10444  -0.0337   1.0000   0.1425
  -8.250  -0.4286   0.10482   0.10091  -0.0321   0.9987   0.1456
  -8.000  -0.3999   0.10164   0.09769  -0.0347   0.9942   0.1534
  -7.750  -0.3994   0.09654   0.09263  -0.0408   0.9866   0.1621
  -7.250  -0.3708   0.08919   0.08528  -0.0479   0.9730   0.1810
  -7.000  -0.3893   0.08480   0.08096  -0.0527   0.9612   0.1927
  -6.750  -0.3956   0.07999   0.07618  -0.0584   0.9498   0.2074
  -6.250  -0.3980   0.04704   0.04071  -0.0921   0.9270   0.0795
  -6.000  -0.3593   0.04262   0.03531  -0.0954   0.9215   0.0691
  -5.750  -0.3175   0.03922   0.03155  -0.0991   0.9182   0.0671
  -5.500  -0.2932   0.03742   0.02943  -0.0992   0.9094   0.0672
  -5.250  -0.2509   0.03551   0.02713  -0.1021   0.9052   0.0687
  -5.000  -0.2234   0.03410   0.02552  -0.1022   0.8977   0.0688
  -4.750  -0.1872   0.03267   0.02392  -0.1034   0.8923   0.0694
  -4.500  -0.1455   0.03114   0.02233  -0.1054   0.8891   0.0711
  -4.250  -0.1277   0.03032   0.02162  -0.1039   0.8795   0.0732
  -4.000  -0.0884   0.02931   0.02071  -0.1057   0.8754   0.0796
  -3.750  -0.0643   0.02873   0.02020  -0.1055   0.8670   0.0878
  -3.500  -0.0229   0.02759   0.01912  -0.1086   0.8620   0.1093
  -3.250   0.0223   0.02686   0.02047  -0.1110   0.8589   0.5705
  -3.000   0.0304   0.02818   0.02178  -0.1061   0.8479   0.5971
  -2.750   0.0464   0.02988   0.02358  -0.0989   0.8434   0.6329
  -2.500   0.0449   0.03122   0.02494  -0.0918   0.8320   0.6582
  -2.250   0.0591   0.03220   0.02593  -0.0845   0.8281   0.6892
  -2.000   0.0564   0.03294   0.02667  -0.0781   0.8167   0.7056
  -1.750   0.0898   0.03266   0.02623  -0.0776   0.8134   0.7208
  -1.500   0.0970   0.03294   0.02646  -0.0745   0.8028   0.7267
  -1.250   0.1454   0.03227   0.02556  -0.0789   0.7993   0.7342
  -1.000   0.1636   0.03230   0.02551  -0.0779   0.7911   0.7385
  -0.750   0.1969   0.03192   0.02501  -0.0791   0.7855   0.7432
  -0.500   0.2486   0.03110   0.02401  -0.0837   0.7832   0.7481
  -0.250   0.2656   0.03147   0.02431  -0.0835   0.7731   0.7520
   0.000   0.3059   0.03081   0.02355  -0.0854   0.7694   0.7554
   0.250   0.3571   0.02997   0.02259  -0.0893   0.7674   0.7595
   0.500   0.3704   0.03055   0.02313  -0.0886   0.7564   0.7629
   0.750   0.4236   0.02980   0.02226  -0.0933   0.7536   0.7668
   1.000   0.4736   0.02899   0.02138  -0.0967   0.7515   0.7702
   1.250   0.4793   0.02968   0.02208  -0.0942   0.7400   0.7733
   1.500   0.5344   0.02889   0.02121  -0.0989   0.7374   0.7772
   1.750   0.5933   0.02809   0.02031  -0.1045   0.7351   0.7814
   2.000   0.5964   0.02882   0.02109  -0.1012   0.7234   0.7843
   2.250   0.6466   0.02803   0.02025  -0.1048   0.7205   0.7876
   2.500   0.6564   0.02878   0.02104  -0.1029   0.7096   0.7915
   2.750   0.7102   0.02807   0.02027  -0.1074   0.7060   0.7959
   3.000   0.7239   0.02863   0.02088  -0.1058   0.6963   0.7993
   3.250   0.7662   0.02807   0.02031  -0.1080   0.6914   0.8028
   3.500   0.8142   0.02748   0.01970  -0.1114   0.6873   0.8073
   3.750   0.8300   0.02814   0.02041  -0.1104   0.6767   0.8119
   4.000   0.8781   0.02737   0.01964  -0.1133   0.6729   0.8159
   4.250   0.8850   0.02818   0.02055  -0.1107   0.6617   0.8200
   4.500   0.9380   0.02743   0.01976  -0.1147   0.6574   0.8250
   4.750   0.9468   0.02821   0.02065  -0.1123   0.6465   0.8298
   5.000   0.9951   0.02746   0.01989  -0.1152   0.6418   0.8350
   5.250   1.0060   0.02824   0.02079  -0.1133   0.6308   0.8405
   5.500   1.0573   0.02746   0.01998  -0.1168   0.6258   0.8456
   5.750   1.0641   0.02822   0.02089  -0.1139   0.6146   0.8516
   6.000   1.0987   0.02815   0.02086  -0.1152   0.6068   0.8584
   6.250   1.1227   0.02815   0.02094  -0.1145   0.5979   0.8652
   6.750   1.1835   0.02796   0.02088  -0.1153   0.5807   0.8803
   7.000   1.1970   0.02847   0.02152  -0.1134   0.5700   0.8895
   7.250   1.2378   0.02786   0.02091  -0.1151   0.5623   0.9003
   7.500   1.2498   0.02815   0.02137  -0.1126   0.5514   0.9133
   7.750   1.2666   0.02828   0.02163  -0.1108   0.5413   0.9301
   8.000   1.3117   0.02745   0.02079  -0.1131   0.5323   0.9562
   8.250   1.3351   0.02786   0.02138  -0.1133   0.5194   1.0000
   8.500   1.3635   0.02822   0.02183  -0.1143   0.5067   1.0000
   8.750   1.3952   0.02841   0.02208  -0.1155   0.4941   1.0000
   9.000   1.4276   0.02849   0.02219  -0.1168   0.4809   1.0000
   9.250   1.4581   0.02857   0.02229  -0.1176   0.4673   1.0000
   9.500   1.4849   0.02871   0.02244  -0.1177   0.4532   1.0000
   9.750   1.5074   0.02894   0.02267  -0.1171   0.4388   1.0000
  10.000   1.5252   0.02926   0.02301  -0.1157   0.4240   1.0000
  10.250   1.5383   0.02965   0.02342  -0.1135   0.4091   1.0000
  10.500   1.5475   0.03018   0.02397  -0.1107   0.3942   1.0000
  10.750   1.5537   0.03084   0.02464  -0.1075   0.3789   1.0000
  11.000   1.5579   0.03164   0.02545  -0.1043   0.3635   1.0000
  11.250   1.5592   0.03261   0.02644  -0.1008   0.3479   1.0000
  11.500   1.5585   0.03376   0.02762  -0.0973   0.3322   1.0000
  11.750   1.5567   0.03510   0.02898  -0.0939   0.3165   1.0000
  12.000   1.5536   0.03664   0.03055  -0.0906   0.3006   1.0000
  12.250   1.5499   0.03838   0.03234  -0.0876   0.2848   1.0000
  12.500   1.5451   0.04035   0.03431  -0.0849   0.2690   1.0000
  12.750   1.5394   0.04254   0.03651  -0.0823   0.2534   1.0000
  13.000   1.5330   0.04495   0.03892  -0.0800   0.2380   1.0000
  13.250   1.5258   0.04759   0.04156  -0.0780   0.2231   1.0000
  13.500   1.5178   0.05047   0.04443  -0.0763   0.2086   1.0000
  13.750   1.5093   0.05358   0.04752  -0.0749   0.1946   1.0000
  14.000   1.5003   0.05693   0.05086  -0.0738   0.1813   1.0000
  14.250   1.4907   0.06051   0.05442  -0.0730   0.1686   1.0000
  14.500   1.4813   0.06427   0.05814  -0.0726   0.1565   1.0000
  14.750   1.4703   0.06846   0.06241  -0.0725   0.1451   1.0000
  15.000   1.4604   0.07277   0.06680  -0.0727   0.1340   1.0000
  15.250   1.4520   0.07702   0.07108  -0.0730   0.1238   1.0000
  15.500   1.4444   0.08125   0.07528  -0.0734   0.1142   1.0000
  15.750   1.4351   0.08590   0.07999  -0.0741   0.1049   1.0000
  16.000   1.4253   0.09083   0.08502  -0.0751   0.0955   1.0000
  16.250   1.4153   0.09583   0.09003  -0.0763   0.0864   1.0000
  16.500   1.4057   0.10079   0.09491  -0.0775   0.0775   1.0000
  16.750   1.3949   0.10625   0.10046  -0.0792   0.0693   1.0000
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