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EPPLER 580 AIRFOIL (e580-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 580 AIRFOIL (e580-il)
Reynolds number: 200,000
Max Cl/Cd: 76.09 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e580-il-200000.txt
Download as CSV file: xf-e580-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3814   0.07792   0.07460  -0.0885   0.9712   0.0699
  -8.750  -0.4031   0.07286   0.06926  -0.0972   0.9548   0.0702
  -8.500  -0.3906   0.06531   0.06186  -0.0986   0.9512   0.0722
  -8.250  -0.3609   0.06279   0.05941  -0.0993   0.9488   0.0744
  -8.000  -0.3534   0.05867   0.05517  -0.1034   0.9395   0.0769
  -7.750  -0.3655   0.05445   0.05004  -0.1114   0.9245   0.0844
  -7.500  -0.3382   0.04918   0.04502  -0.1130   0.9220   0.0868
  -7.250  -0.3071   0.04620   0.04200  -0.1161   0.9194   0.0916
  -7.000  -0.2947   0.04311   0.03860  -0.1179   0.9097   0.1016
  -6.750  -0.2583   0.03124   0.02499  -0.1198   0.9064   0.0445
  -6.500  -0.2204   0.02772   0.02105  -0.1222   0.9047   0.0415
  -6.250  -0.1957   0.02569   0.01868  -0.1216   0.8971   0.0401
  -6.000  -0.1598   0.02394   0.01676  -0.1230   0.8938   0.0398
  -5.750  -0.1209   0.02240   0.01512  -0.1249   0.8917   0.0402
  -5.500  -0.0796   0.02104   0.01373  -0.1274   0.8901   0.0412
  -5.250  -0.0516   0.02026   0.01293  -0.1276   0.8829   0.0435
  -5.000  -0.0137   0.01925   0.01188  -0.1296   0.8788   0.0453
  -4.750   0.0283   0.01820   0.01078  -0.1324   0.8759   0.0469
  -4.500   0.0641   0.01694   0.00954  -0.1349   0.8703   0.0506
  -4.250   0.0995   0.01617   0.00871  -0.1368   0.8634   0.0562
  -4.000   0.1512   0.01294   0.00696  -0.1453   0.8599   0.3804
  -3.750   0.1807   0.01330   0.00762  -0.1450   0.8510   0.5245
  -3.500   0.2170   0.01373   0.00797  -0.1457   0.8450   0.5540
  -3.250   0.2440   0.01422   0.00840  -0.1448   0.8359   0.5728
  -3.000   0.2744   0.01500   0.00918  -0.1437   0.8291   0.5959
  -2.750   0.2915   0.01605   0.01034  -0.1395   0.8192   0.6146
  -2.500   0.3206   0.01660   0.01083  -0.1383   0.8126   0.6289
  -2.250   0.3441   0.01665   0.01082  -0.1372   0.8026   0.6337
  -2.000   0.3814   0.01637   0.01033  -0.1398   0.7956   0.6400
  -1.750   0.4074   0.01626   0.01014  -0.1395   0.7861   0.6431
  -1.500   0.4366   0.01620   0.00999  -0.1397   0.7785   0.6457
  -1.250   0.4645   0.01612   0.00983  -0.1398   0.7698   0.6491
  -1.000   0.4955   0.01600   0.00958  -0.1408   0.7619   0.6530
  -0.750   0.5277   0.01583   0.00927  -0.1423   0.7537   0.6573
  -0.500   0.5546   0.01579   0.00919  -0.1421   0.7459   0.6595
  -0.250   0.5827   0.01575   0.00909  -0.1422   0.7381   0.6619
   0.000   0.6109   0.01573   0.00901  -0.1425   0.7304   0.6648
   0.250   0.6406   0.01569   0.00888  -0.1432   0.7227   0.6686
   0.500   0.6721   0.01564   0.00873  -0.1445   0.7152   0.6724
   0.750   0.6991   0.01561   0.00867  -0.1444   0.7075   0.6745
   1.000   0.7268   0.01564   0.00867  -0.1444   0.7005   0.6770
   1.250   0.7535   0.01567   0.00868  -0.1444   0.6926   0.6800
   1.500   0.7835   0.01570   0.00864  -0.1450   0.6859   0.6833
   1.750   0.8114   0.01572   0.00863  -0.1454   0.6779   0.6866
   2.000   0.8424   0.01574   0.00857  -0.1463   0.6715   0.6894
   2.250   0.8660   0.01579   0.00868  -0.1456   0.6632   0.6920
   2.500   0.8965   0.01586   0.00868  -0.1462   0.6570   0.6951
   2.750   0.9206   0.01594   0.00882  -0.1457   0.6486   0.6982
   3.000   0.9520   0.01600   0.00879  -0.1467   0.6421   0.7016
   3.250   0.9771   0.01608   0.00893  -0.1464   0.6338   0.7048
   3.500   1.0053   0.01615   0.00897  -0.1465   0.6270   0.7076
   3.750   1.0292   0.01627   0.00916  -0.1459   0.6189   0.7109
   4.000   1.0582   0.01635   0.00922  -0.1464   0.6117   0.7145
   4.250   1.0837   0.01648   0.00938  -0.1462   0.6033   0.7182
   4.500   1.1120   0.01656   0.00944  -0.1464   0.5959   0.7213
   4.750   1.1347   0.01669   0.00966  -0.1456   0.5874   0.7246
   5.000   1.1628   0.01681   0.00976  -0.1458   0.5799   0.7286
   5.250   1.1862   0.01696   0.00999  -0.1451   0.5708   0.7330
   5.500   1.2150   0.01708   0.01006  -0.1455   0.5631   0.7366
   5.750   1.2352   0.01720   0.01033  -0.1442   0.5534   0.7401
   6.000   1.2604   0.01735   0.01049  -0.1438   0.5448   0.7444
   6.250   1.2843   0.01749   0.01066  -0.1433   0.5352   0.7495
   6.500   1.3056   0.01764   0.01090  -0.1421   0.5255   0.7538
   6.750   1.3307   0.01779   0.01105  -0.1417   0.5164   0.7586
   7.000   1.3499   0.01796   0.01133  -0.1403   0.5055   0.7640
   7.250   1.3705   0.01814   0.01158  -0.1391   0.4952   0.7689
   7.500   1.3923   0.01832   0.01177  -0.1381   0.4850   0.7744
   7.750   1.4103   0.01854   0.01208  -0.1365   0.4734   0.7812
   8.000   1.4266   0.01875   0.01240  -0.1344   0.4620   0.7873
   8.250   1.4443   0.01901   0.01271  -0.1328   0.4505   0.7952
   8.500   1.4601   0.01927   0.01300  -0.1307   0.4388   0.8025
   8.750   1.4724   0.01956   0.01337  -0.1281   0.4264   0.8116
   9.000   1.4831   0.01989   0.01381  -0.1251   0.4139   0.8208
   9.250   1.4942   0.02029   0.01428  -0.1224   0.4012   0.8321
   9.500   1.5037   0.02073   0.01479  -0.1194   0.3880   0.8462
   9.750   1.5113   0.02121   0.01533  -0.1162   0.3745   0.8644
  10.000   1.5152   0.02168   0.01589  -0.1123   0.3609   0.8953
  10.250   1.5180   0.02220   0.01648  -0.1086   0.3464   1.0000
  10.500   1.5269   0.02315   0.01742  -0.1065   0.3296   1.0000
  10.750   1.5332   0.02423   0.01847  -0.1041   0.3125   1.0000
  11.000   1.5370   0.02546   0.01968  -0.1015   0.2947   1.0000
  11.250   1.5389   0.02688   0.02105  -0.0988   0.2768   1.0000
  11.500   1.5394   0.02849   0.02261  -0.0961   0.2594   1.0000
  11.750   1.5398   0.03023   0.02432  -0.0937   0.2424   1.0000
  12.000   1.5394   0.03216   0.02622  -0.0914   0.2244   1.0000
  12.250   1.5379   0.03428   0.02834  -0.0893   0.2074   1.0000
  12.500   1.5355   0.03661   0.03063  -0.0874   0.1912   1.0000
  12.750   1.5324   0.03915   0.03314  -0.0857   0.1758   1.0000
  13.000   1.5293   0.04182   0.03580  -0.0843   0.1615   1.0000
  13.250   1.5261   0.04465   0.03861  -0.0830   0.1481   1.0000
  13.500   1.5229   0.04760   0.04157  -0.0820   0.1358   1.0000
  13.750   1.5196   0.05069   0.04467  -0.0812   0.1246   1.0000
  14.000   1.5151   0.05404   0.04802  -0.0806   0.1143   1.0000
  14.250   1.5105   0.05753   0.05152  -0.0802   0.1043   1.0000
  14.500   1.5075   0.06096   0.05500  -0.0800   0.0941   1.0000
  14.750   1.5028   0.06469   0.05876  -0.0799   0.0843   1.0000
  15.000   1.4965   0.06876   0.06286  -0.0800   0.0747   1.0000
  15.250   1.4882   0.07323   0.06734  -0.0804   0.0647   1.0000
  15.500   1.4774   0.07817   0.07228  -0.0810   0.0546   1.0000
  15.750   1.4640   0.08366   0.07776  -0.0819   0.0452   1.0000
  16.000   1.4483   0.08966   0.08376  -0.0832   0.0383   1.0000
  16.250   1.4369   0.09519   0.08937  -0.0844   0.0329   1.0000
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