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EPPLER 583 AIRFOIL (e583-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 583 AIRFOIL (e583-il)
Reynolds number: 500,000
Max Cl/Cd: 107.74 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e583-il-500000-n5.txt
Download as CSV file: xf-e583-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 583 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.1227   0.07902   0.07535  -0.1171   0.7362   0.0049
 -10.750  -0.1544   0.06601   0.06237  -0.1233   0.7276   0.0047
 -10.250  -0.2857   0.03900   0.03491  -0.1334   0.7186   0.0044
 -10.000  -0.3372   0.03295   0.02839  -0.1279   0.7138   0.0044
  -9.750  -0.3563   0.03029   0.02544  -0.1230   0.7091   0.0043
  -9.500  -0.3693   0.02698   0.02167  -0.1186   0.7047   0.0044
  -9.250  -0.3643   0.02511   0.01949  -0.1161   0.7008   0.0044
  -9.000  -0.3556   0.02329   0.01734  -0.1138   0.6974   0.0045
  -8.750  -0.3411   0.02202   0.01585  -0.1123   0.6941   0.0046
  -8.500  -0.3249   0.02080   0.01442  -0.1109   0.6908   0.0046
  -8.250  -0.3065   0.01979   0.01317  -0.1097   0.6875   0.0048
  -8.000  -0.2875   0.01887   0.01208  -0.1086   0.6846   0.0049
  -7.750  -0.2684   0.01795   0.01103  -0.1076   0.6818   0.0051
  -7.500  -0.2466   0.01734   0.01034  -0.1069   0.6788   0.0053
  -7.250  -0.2245   0.01676   0.00968  -0.1062   0.6757   0.0054
  -7.000  -0.2018   0.01626   0.00910  -0.1056   0.6728   0.0057
  -6.750  -0.1792   0.01572   0.00847  -0.1049   0.6702   0.0058
  -6.500  -0.1559   0.01529   0.00794  -0.1043   0.6678   0.0062
  -6.250  -0.1327   0.01484   0.00741  -0.1037   0.6655   0.0064
  -6.000  -0.1090   0.01440   0.00691  -0.1032   0.6632   0.0066
  -5.750  -0.0849   0.01402   0.00648  -0.1027   0.6605   0.0068
  -5.500  -0.0612   0.01361   0.00603  -0.1022   0.6579   0.0073
  -5.250  -0.0367   0.01329   0.00567  -0.1018   0.6554   0.0077
  -5.000  -0.0116   0.01305   0.00539  -0.1015   0.6532   0.0086
  -4.750   0.0133   0.01279   0.00506  -0.1011   0.6510   0.0094
  -4.500   0.0383   0.01250   0.00474  -0.1008   0.6488   0.0104
  -4.000   0.0892   0.01197   0.00418  -0.1003   0.6442   0.0142
  -3.750   0.1147   0.01173   0.00394  -0.1000   0.6418   0.0193
  -3.500   0.1403   0.01149   0.00375  -0.0998   0.6394   0.0308
  -3.250   0.1658   0.01126   0.00358  -0.0996   0.6372   0.0497
  -3.000   0.1913   0.01101   0.00342  -0.0995   0.6351   0.0790
  -2.750   0.2167   0.01074   0.00329  -0.0994   0.6329   0.1196
  -2.500   0.2416   0.01036   0.00316  -0.0992   0.6308   0.1867
  -2.250   0.2659   0.00989   0.00303  -0.0991   0.6285   0.2858
  -2.000   0.2900   0.00933   0.00288  -0.0991   0.6261   0.4097
  -1.750   0.3130   0.00856   0.00271  -0.0988   0.6238   0.5895
  -1.500   0.3376   0.00838   0.00290  -0.0982   0.6216   0.7098
  -1.250   0.3653   0.00847   0.00296  -0.0981   0.6194   0.7367
  -1.000   0.3934   0.00856   0.00301  -0.0982   0.6172   0.7520
  -0.750   0.4213   0.00862   0.00306  -0.0983   0.6149   0.7621
  -0.500   0.4488   0.00873   0.00316  -0.0982   0.6124   0.7766
  -0.250   0.4750   0.00893   0.00338  -0.0977   0.6098   0.7936
   0.000   0.5017   0.00908   0.00351  -0.0974   0.6073   0.8034
   0.250   0.5304   0.00912   0.00348  -0.0977   0.6048   0.8062
   0.500   0.5585   0.00917   0.00347  -0.0980   0.6024   0.8078
   0.750   0.5865   0.00920   0.00349  -0.0982   0.5999   0.8091
   1.000   0.6142   0.00922   0.00352  -0.0984   0.5971   0.8105
   1.250   0.6421   0.00926   0.00355  -0.0986   0.5943   0.8120
   1.500   0.6699   0.00929   0.00356  -0.0988   0.5913   0.8135
   1.750   0.6977   0.00934   0.00358  -0.0990   0.5886   0.8149
   2.000   0.7256   0.00941   0.00360  -0.0992   0.5859   0.8165
   2.250   0.7532   0.00944   0.00366  -0.0994   0.5828   0.8183
   2.500   0.7809   0.00948   0.00371  -0.0997   0.5794   0.8200
   2.750   0.8084   0.00953   0.00374  -0.0999   0.5757   0.8215
   3.000   0.8358   0.00959   0.00378  -0.1001   0.5721   0.8229
   3.250   0.8626   0.00964   0.00383  -0.1001   0.5685   0.8241
   3.500   0.8891   0.00968   0.00391  -0.1001   0.5640   0.8253
   3.750   0.9151   0.00974   0.00398  -0.1000   0.5594   0.8268
   4.000   0.9408   0.00982   0.00405  -0.0998   0.5550   0.8284
   4.250   0.9669   0.00988   0.00415  -0.0997   0.5500   0.8300
   4.500   0.9924   0.00995   0.00424  -0.0995   0.5446   0.8315
   4.750   1.0173   0.01005   0.00432  -0.0992   0.5394   0.8332
   5.000   1.0428   0.01012   0.00444  -0.0991   0.5332   0.8348
   5.250   1.0670   0.01023   0.00454  -0.0987   0.5265   0.8366
   5.500   1.0913   0.01034   0.00467  -0.0983   0.5195   0.8383
   5.750   1.1143   0.01046   0.00480  -0.0977   0.5115   0.8399
   6.000   1.1363   0.01059   0.00495  -0.0968   0.5033   0.8416
   6.250   1.1562   0.01076   0.00512  -0.0956   0.4941   0.8435
   6.500   1.1765   0.01092   0.00530  -0.0944   0.4843   0.8455
   6.750   1.1935   0.01111   0.00549  -0.0926   0.4745   0.8477
   7.000   1.2086   0.01136   0.00573  -0.0905   0.4636   0.8500
   7.250   1.2247   0.01164   0.00600  -0.0886   0.4516   0.8524
   7.500   1.2398   0.01196   0.00631  -0.0867   0.4399   0.8548
   7.750   1.2531   0.01233   0.00667  -0.0843   0.4279   0.8570
   8.000   1.2646   0.01274   0.00708  -0.0818   0.4154   0.8595
   8.250   1.2756   0.01320   0.00754  -0.0792   0.4023   0.8625
   8.500   1.2863   0.01371   0.00804  -0.0768   0.3889   0.8658
   8.750   1.2947   0.01433   0.00864  -0.0740   0.3742   0.8694
   9.000   1.3018   0.01503   0.00933  -0.0712   0.3595   0.8726
   9.250   1.3050   0.01591   0.01018  -0.0680   0.3426   0.8761
   9.500   1.3103   0.01680   0.01106  -0.0652   0.3282   0.8801
   9.750   1.3138   0.01786   0.01210  -0.0624   0.3127   0.8844
  10.000   1.3186   0.01893   0.01318  -0.0599   0.2993   0.8886
  10.250   1.3207   0.02019   0.01442  -0.0573   0.2842   0.8936
  10.500   1.3229   0.02153   0.01575  -0.0548   0.2696   0.8995
  10.750   1.3250   0.02292   0.01714  -0.0525   0.2559   0.9061
  11.000   1.3271   0.02434   0.01856  -0.0502   0.2429   0.9145
  11.250   1.3285   0.02585   0.02009  -0.0480   0.2296   0.9252
  11.500   1.3322   0.02747   0.02171  -0.0465   0.2158   0.9424
  12.000   1.3409   0.03104   0.02525  -0.0445   0.1869   1.0000
  12.250   1.3428   0.03301   0.02716  -0.0432   0.1721   1.0000
  12.500   1.3447   0.03502   0.02913  -0.0419   0.1581   1.0000
  12.750   1.3470   0.03706   0.03113  -0.0409   0.1455   1.0000
  13.000   1.3499   0.03909   0.03313  -0.0399   0.1332   1.0000
  13.250   1.3541   0.04106   0.03509  -0.0391   0.1227   1.0000
  13.500   1.3584   0.04307   0.03710  -0.0383   0.1136   1.0000
  13.750   1.3611   0.04527   0.03928  -0.0376   0.1034   1.0000
  14.000   1.3632   0.04758   0.04158  -0.0370   0.0940   1.0000
  14.250   1.3674   0.04973   0.04373  -0.0364   0.0853   1.0000
  14.500   1.3697   0.05212   0.04612  -0.0360   0.0768   1.0000
  14.750   1.3720   0.05457   0.04856  -0.0356   0.0692   1.0000
  15.000   1.3732   0.05718   0.05116  -0.0353   0.0616   1.0000
  15.250   1.3749   0.05980   0.05379  -0.0350   0.0544   1.0000
  15.500   1.3775   0.06236   0.05637  -0.0349   0.0486   1.0000
  15.750   1.3783   0.06520   0.05923  -0.0349   0.0431   1.0000
  16.000   1.3796   0.06803   0.06208  -0.0349   0.0381   1.0000
  16.250   1.3809   0.07093   0.06501  -0.0351   0.0336   1.0000
  16.500   1.3814   0.07395   0.06807  -0.0353   0.0294   1.0000
  16.750   1.3815   0.07710   0.07125  -0.0356   0.0260   1.0000
  17.000   1.3822   0.08024   0.07444  -0.0361   0.0231   1.0000
  17.250   1.3818   0.08357   0.07782  -0.0366   0.0199   1.0000
  17.500   1.3806   0.08706   0.08135  -0.0373   0.0174   1.0000
  17.750   1.3805   0.09045   0.08481  -0.0380   0.0156   1.0000
  18.000   1.3805   0.09387   0.08830  -0.0388   0.0141   1.0000
  18.500   1.3769   0.10140   0.09595  -0.0409   0.0107   1.0000
  18.750   1.3753   0.10519   0.09981  -0.0421   0.0095   1.0000
  19.000   1.3739   0.10898   0.10368  -0.0433   0.0083   1.0000
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