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EPPLER 58 AIRFOIL (e58-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 58 AIRFOIL (e58-il)
Reynolds number: 1,000,000
Max Cl/Cd: 160.82 at α=0°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e58-il-1000000-n5.txt
Download as CSV file: xf-e58-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 58 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250   0.0099   0.09205   0.09016  -0.1204   0.9694   0.0043
 -11.000   0.0197   0.08884   0.08696  -0.1221   0.9691   0.0053
 -10.500  -0.0750   0.10451   0.10254  -0.1134   0.9706   0.0044
 -10.250  -0.0626   0.10128   0.09931  -0.1159   0.9701   0.0043
 -10.000  -0.0493   0.09830   0.09633  -0.1184   0.9696   0.0047
  -9.750  -0.0354   0.09516   0.09319  -0.1212   0.9692   0.0049
  -9.500  -0.0304   0.09281   0.09085  -0.1212   0.9663   0.0050
  -9.250  -0.0196   0.08976   0.08780  -0.1231   0.9641   0.0056
  -8.250   0.0374   0.07589   0.07392  -0.1357   0.9594   0.0035
  -8.000   0.0551   0.07261   0.07064  -0.1398   0.9583   0.0033
  -7.750   0.0670   0.06952   0.06756  -0.1423   0.9557   0.0033
  -7.500   0.0709   0.06698   0.06503  -0.1425   0.9510   0.0033
  -7.250   0.0826   0.06428   0.06232  -0.1447   0.9480   0.0032
  -6.750   0.1096   0.05688   0.05492  -0.1525   0.9413   0.0034
  -6.250   0.2313   0.01266   0.00921  -0.2261   0.9274   0.0037
  -6.000   0.2651   0.01106   0.00729  -0.2287   0.9262   0.0040
  -5.750   0.2948   0.01052   0.00664  -0.2296   0.9250   0.0044
  -5.500   0.3255   0.00989   0.00586  -0.2306   0.9239   0.0048
  -5.250   0.3570   0.00917   0.00494  -0.2318   0.9228   0.0053
  -5.000   0.3880   0.00866   0.00428  -0.2328   0.9214   0.0057
  -4.750   0.4199   0.00806   0.00352  -0.2339   0.9198   0.0066
  -4.500   0.4511   0.00773   0.00312  -0.2348   0.9182   0.0077
  -4.250   0.4808   0.00750   0.00281  -0.2353   0.9162   0.0090
  -4.000   0.5086   0.00723   0.00253  -0.2354   0.9136   0.0122
  -3.750   0.5364   0.00711   0.00242  -0.2354   0.9108   0.0153
  -3.500   0.5649   0.00699   0.00230  -0.2356   0.9076   0.0196
  -3.250   0.5946   0.00691   0.00219  -0.2360   0.9043   0.0241
  -3.000   0.6214   0.00688   0.00214  -0.2357   0.8997   0.0264
  -2.750   0.6482   0.00686   0.00211  -0.2355   0.8950   0.0274
  -2.500   0.6769   0.00682   0.00204  -0.2357   0.8912   0.0278
  -2.250   0.7067   0.00658   0.00173  -0.2362   0.8883   0.0289
  -2.000   0.7346   0.00645   0.00157  -0.2363   0.8846   0.0293
  -1.750   0.7631   0.00632   0.00141  -0.2365   0.8805   0.0301
  -1.500   0.7924   0.00623   0.00127  -0.2369   0.8764   0.0302
  -1.250   0.8197   0.00617   0.00120  -0.2368   0.8715   0.0302
  -1.000   0.8477   0.00611   0.00110  -0.2368   0.8653   0.0303
  -0.750   0.8751   0.00607   0.00102  -0.2367   0.8562   0.0306
  -0.500   0.9025   0.00605   0.00095  -0.2366   0.8454   0.0318
  -0.250   0.9296   0.00605   0.00092  -0.2364   0.8330   0.0358
   0.000   0.9569   0.00595   0.00094  -0.2364   0.8141   0.1164
   0.250   0.9795   0.00614   0.00100  -0.2352   0.7768   0.1345
   0.500   0.9943   0.00668   0.00121  -0.2323   0.7052   0.1458
   0.750   1.0097   0.00727   0.00150  -0.2296   0.6429   0.1534
   1.000   1.0304   0.00763   0.00171  -0.2282   0.6080   0.1617
   1.250   1.0504   0.00805   0.00195  -0.2266   0.5621   0.1717
   1.500   1.0661   0.00878   0.00230  -0.2242   0.4759   0.1839
   1.750   1.0852   0.00937   0.00264  -0.2226   0.4151   0.2043
   2.000   1.1079   0.00975   0.00294  -0.2218   0.3707   0.2725
   2.250   1.1343   0.00990   0.00330  -0.2221   0.3290   0.4834
   2.500   1.1605   0.01007   0.00379  -0.2222   0.2826   0.7488
   2.750   1.1820   0.01022   0.00409  -0.2210   0.2600   0.8837
   3.000   1.1985   0.01058   0.00435  -0.2187   0.2154   1.0000
   3.250   1.2184   0.01131   0.00476  -0.2173   0.1581   1.0000
   3.500   1.2415   0.01169   0.00507  -0.2165   0.1381   1.0000
   3.750   1.2610   0.01250   0.00554  -0.2151   0.0753   1.0000
   4.000   1.2831   0.01301   0.00594  -0.2140   0.0517   1.0000
   4.250   1.3036   0.01371   0.00644  -0.2127   0.0162   1.0000
   4.500   1.3267   0.01409   0.00682  -0.2119   0.0096   1.0000
   4.750   1.3497   0.01446   0.00723  -0.2110   0.0076   1.0000
   5.000   1.3719   0.01490   0.00770  -0.2099   0.0060   1.0000
   5.250   1.3939   0.01529   0.00812  -0.2088   0.0052   1.0000
   5.500   1.4153   0.01573   0.00858  -0.2076   0.0045   1.0000
   5.750   1.4357   0.01629   0.00918  -0.2062   0.0038   1.0000
   6.000   1.4566   0.01675   0.00971  -0.2049   0.0034   1.0000
   6.250   1.4768   0.01728   0.01028  -0.2035   0.0031   1.0000
   6.500   1.4967   0.01784   0.01089  -0.2021   0.0028   1.0000
   6.750   1.5160   0.01844   0.01153  -0.2006   0.0026   1.0000
   7.000   1.5326   0.01940   0.01258  -0.1985   0.0023   1.0000
   7.250   1.5499   0.02019   0.01344  -0.1966   0.0022   1.0000
   7.500   1.5667   0.02102   0.01436  -0.1945   0.0021   1.0000
   7.750   1.5823   0.02195   0.01540  -0.1923   0.0020   1.0000
   8.000   1.5975   0.02292   0.01646  -0.1901   0.0018   1.0000
   8.250   1.6129   0.02384   0.01747  -0.1880   0.0017   1.0000
   8.500   1.6286   0.02470   0.01844  -0.1860   0.0016   1.0000
   8.750   1.6443   0.02553   0.01934  -0.1841   0.0015   1.0000
   9.000   1.6583   0.02658   0.02048  -0.1819   0.0014   1.0000
   9.250   1.6711   0.02774   0.02174  -0.1795   0.0013   1.0000
   9.500   1.6813   0.02928   0.02341  -0.1767   0.0013   1.0000
   9.750   1.6888   0.03122   0.02552  -0.1736   0.0012   1.0000
  10.000   1.6968   0.03316   0.02764  -0.1706   0.0012   1.0000
  10.250   1.7053   0.03504   0.02971  -0.1678   0.0011   1.0000
  10.500   1.7131   0.03696   0.03181  -0.1649   0.0011   1.0000
  10.750   1.7170   0.03956   0.03466  -0.1616   0.0011   1.0000
  11.000   1.7210   0.04195   0.03725  -0.1585   0.0011   1.0000
  11.250   1.7201   0.04519   0.04078  -0.1549   0.0010   1.0000
  11.500   1.7126   0.04940   0.04532  -0.1507   0.0010   1.0000
  11.750   1.6992   0.05448   0.05076  -0.1462   0.0009   1.0000
  12.000   1.6826   0.05981   0.05642  -0.1421   0.0008   1.0000
  12.250   1.6507   0.06767   0.06470  -0.1377   0.0008   1.0000
  12.500   1.6189   0.07544   0.07280  -0.1348   0.0008   1.0000
  12.750   1.5959   0.08205   0.07966  -0.1335   0.0008   1.0000
  13.000   1.5744   0.08884   0.08667  -0.1335   0.0007   1.0000
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