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E61 (5.64%) (e61-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E61 (5.64%) (e61-il)
Reynolds number: 50,000
Max Cl/Cd: 45.43 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e61-il-50000-n5.txt
Download as CSV file: xf-e61-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E61  (5.64%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.3405   0.11628   0.11015  -0.0189   1.0000   0.0623
  -6.500  -0.3508   0.11583   0.10980  -0.0173   1.0000   0.0632
  -6.250  -0.3568   0.11518   0.10925  -0.0174   1.0000   0.0638
  -6.000  -0.3599   0.11445   0.10862  -0.0192   1.0000   0.0642
  -5.750  -0.3578   0.11322   0.10746  -0.0223   1.0000   0.0645
  -5.500  -0.3564   0.10750   0.10180  -0.0166   1.0000   0.0660
  -5.250  -0.3519   0.10412   0.09844  -0.0147   0.9994   0.0691
  -5.000  -0.3308   0.10096   0.09527  -0.0203   0.9942   0.0749
  -4.750  -0.2921   0.09841   0.09272  -0.0365   0.9862   0.0785
  -4.500  -0.2880   0.09364   0.08797  -0.0307   0.9837   0.0825
  -4.250  -0.2657   0.09035   0.08465  -0.0359   0.9780   0.0882
  -4.000  -0.2227   0.08639   0.08063  -0.0497   0.9722   0.0926
  -3.750  -0.2121   0.08269   0.07695  -0.0482   0.9677   0.0958
  -3.500  -0.1538   0.07874   0.07284  -0.0656   0.9622   0.1058
  -3.250  -0.1436   0.07485   0.06899  -0.0631   0.9585   0.1090
  -3.000  -0.0931   0.07087   0.06486  -0.0757   0.9536   0.1202
  -2.750  -0.0719   0.06740   0.06130  -0.0764   0.9496   0.1260
  -2.500  -0.0246   0.06342   0.05719  -0.0856   0.9464   0.1386
  -2.000   0.1558   0.04987   0.04245  -0.1227   0.9452   0.0635
  -1.750   0.2068   0.04619   0.03853  -0.1300   0.9426   0.0586
  -1.500   0.2829   0.04167   0.03320  -0.1423   0.9424   0.0532
  -1.250   0.3438   0.03894   0.02953  -0.1498   0.9407   0.0507
  -1.000   0.3917   0.03697   0.02702  -0.1546   0.9383   0.0504
  -0.750   0.4377   0.03552   0.02496  -0.1586   0.9360   0.0506
  -0.500   0.4753   0.03447   0.02357  -0.1610   0.9317   0.0517
  -0.250   0.5101   0.03389   0.02276  -0.1628   0.9268   0.0588
   0.000   0.5483   0.03339   0.02197  -0.1649   0.9232   0.0690
   0.250   0.5797   0.03307   0.02139  -0.1657   0.9170   0.0781
   0.500   0.6186   0.03259   0.02091  -0.1682   0.9125   0.1092
   0.750   0.6525   0.03053   0.02092  -0.1697   0.9091   1.0000
   1.000   0.6784   0.03096   0.02095  -0.1696   0.9003   1.0000
   1.250   0.7122   0.03131   0.02096  -0.1709   0.8942   1.0000
   1.750   0.7705   0.03208   0.02132  -0.1720   0.8783   1.0000
   2.000   0.8036   0.03236   0.02146  -0.1732   0.8713   1.0000
   2.250   0.8301   0.03277   0.02179  -0.1732   0.8620   1.0000
   2.500   0.8678   0.03288   0.02185  -0.1750   0.8562   1.0000
   2.750   0.8925   0.03329   0.02225  -0.1747   0.8457   1.0000
   3.000   0.9201   0.03362   0.02258  -0.1748   0.8359   1.0000
   3.250   0.9583   0.03354   0.02253  -0.1764   0.8295   1.0000
   3.500   0.9839   0.03386   0.02291  -0.1760   0.8181   1.0000
   3.750   1.0114   0.03408   0.02329  -0.1759   0.8070   1.0000
   4.000   1.0415   0.03413   0.02345  -0.1760   0.7965   1.0000
   4.250   1.0811   0.03363   0.02310  -0.1773   0.7889   1.0000
   4.500   1.1093   0.03361   0.02324  -0.1768   0.7764   1.0000
   4.750   1.1389   0.03345   0.02338  -0.1765   0.7636   1.0000
   5.000   1.1699   0.03315   0.02331  -0.1762   0.7502   1.0000
   5.250   1.2023   0.03271   0.02310  -0.1759   0.7361   1.0000
   5.500   1.2368   0.03208   0.02275  -0.1758   0.7209   1.0000
   5.750   1.2591   0.03208   0.02300  -0.1740   0.7001   1.0000
   6.000   1.2946   0.03126   0.02261  -0.1736   0.6798   1.0000
   6.250   1.3195   0.03102   0.02264  -0.1719   0.6532   1.0000
   6.500   1.3429   0.03087   0.02274  -0.1699   0.6213   1.0000
   6.750   1.3685   0.03062   0.02269  -0.1680   0.5815   1.0000
   7.000   1.3915   0.03063   0.02278  -0.1657   0.5313   1.0000
   7.250   1.4106   0.03110   0.02315  -0.1630   0.4715   1.0000
   7.500   1.4218   0.03223   0.02409  -0.1595   0.4093   1.0000
   7.750   1.4265   0.03389   0.02551  -0.1556   0.3490   1.0000
   8.000   1.4266   0.03598   0.02733  -0.1515   0.2882   1.0000
   8.250   1.4213   0.03865   0.02971  -0.1473   0.2195   1.0000
   8.500   1.4148   0.04183   0.03226  -0.1437   0.1468   1.0000
   8.750   1.4103   0.04542   0.03517  -0.1406   0.0814   1.0000
   9.000   1.4094   0.04901   0.03856  -0.1376   0.0526   1.0000
   9.250   1.4107   0.05231   0.04192  -0.1348   0.0408   1.0000
   9.500   1.4123   0.05551   0.04516  -0.1325   0.0339   1.0000
   9.750   1.4188   0.05830   0.04833  -0.1303   0.0290   1.0000
  10.000   1.4239   0.06132   0.05159  -0.1282   0.0261   1.0000
  10.250   1.4291   0.06460   0.05508  -0.1262   0.0244   1.0000
  10.500   1.4392   0.06820   0.05889  -0.1243   0.0230   1.0000
  10.750   1.4557   0.07155   0.06270  -0.1226   0.0221   1.0000
  11.000   1.4669   0.07547   0.06709  -0.1210   0.0214   1.0000
  11.250   1.4704   0.07987   0.07195  -0.1194   0.0210   1.0000
  11.500   1.4674   0.08460   0.07712  -0.1180   0.0208   1.0000
  11.750   1.4595   0.08965   0.08257  -0.1170   0.0207   1.0000
  12.000   1.4476   0.09510   0.08840  -0.1165   0.0206   1.0000
  12.250   1.4339   0.10079   0.09444  -0.1168   0.0206   1.0000
  12.500   1.4185   0.10683   0.10080  -0.1179   0.0206   1.0000
  12.750   1.4021   0.11330   0.10755  -0.1199   0.0207   1.0000
  13.000   1.3850   0.12033   0.11484  -0.1230   0.0208   1.0000
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