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NACA M18 AIRFOIL (m18-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA M18 AIRFOIL (m18-il)
Reynolds number: 50,000
Max Cl/Cd: 25.27 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m18-il-50000-n5.txt
Download as CSV file: xf-m18-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M18 AIRFOIL                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3734   0.11892   0.11213  -0.0162   1.0000   0.1243
  -9.500  -0.3831   0.11708   0.11039  -0.0203   1.0000   0.1277
  -9.250  -0.3964   0.11515   0.10859  -0.0253   1.0000   0.1286
  -9.000  -0.3758   0.10956   0.10301  -0.0239   1.0000   0.1302
  -8.750  -0.3604   0.10552   0.09899  -0.0235   1.0000   0.1327
  -8.500  -0.3530   0.10219   0.09572  -0.0245   1.0000   0.1355
  -8.250  -0.3505   0.09907   0.09267  -0.0264   1.0000   0.1385
  -8.000  -0.3609   0.09652   0.09025  -0.0301   1.0000   0.1427
  -7.500  -0.4113   0.09464   0.08863  -0.0327   0.9995   0.1450
  -7.250  -0.3784   0.08849   0.08253  -0.0326   0.9913   0.1473
  -6.750  -0.3465   0.07540   0.06872  -0.0500   0.9507   0.0977
  -6.250  -0.3050   0.06514   0.05805  -0.0556   0.9242   0.0823
  -6.000  -0.2841   0.06161   0.05439  -0.0570   0.9118   0.0807
  -5.750  -0.2671   0.05832   0.05089  -0.0578   0.8978   0.0791
  -5.500  -0.2509   0.05515   0.04746  -0.0581   0.8842   0.0776
  -5.250  -0.2347   0.05213   0.04413  -0.0579   0.8712   0.0765
  -5.000  -0.2173   0.04947   0.04115  -0.0575   0.8593   0.0768
  -4.750  -0.1987   0.04701   0.03833  -0.0568   0.8485   0.0776
  -4.500  -0.1810   0.04475   0.03573  -0.0559   0.8363   0.0782
  -4.250  -0.1617   0.04253   0.03314  -0.0549   0.8255   0.0781
  -4.000  -0.1405   0.04037   0.03056  -0.0538   0.8163   0.0778
  -3.750  -0.1196   0.03851   0.02834  -0.0528   0.8053   0.0777
  -3.500  -0.0965   0.03674   0.02617  -0.0518   0.7962   0.0780
  -3.250  -0.0728   0.03515   0.02421  -0.0509   0.7866   0.0785
  -3.000  -0.0481   0.03378   0.02247  -0.0502   0.7772   0.0799
  -2.500   0.0040   0.03150   0.01960  -0.0491   0.7592   0.0851
  -2.250   0.0316   0.03050   0.01843  -0.0486   0.7514   0.0875
  -2.000   0.0599   0.02968   0.01744  -0.0486   0.7418   0.0900
  -1.750   0.0935   0.02878   0.01630  -0.0489   0.7347   0.0936
  -1.500   0.1270   0.02815   0.01547  -0.0497   0.7251   0.0987
  -1.250   0.1581   0.02753   0.01481  -0.0499   0.7182   0.1074
  -1.000   0.1850   0.02713   0.01438  -0.0498   0.7087   0.1173
  -0.750   0.2115   0.02657   0.01376  -0.0490   0.7021   0.1317
  -0.250   0.3643   0.02315   0.01286  -0.0665   0.6865   1.0000
   0.250   0.4113   0.02359   0.01278  -0.0650   0.6707   1.0000
   0.500   0.4341   0.02392   0.01293  -0.0643   0.6623   1.0000
   0.750   0.4572   0.02414   0.01295  -0.0634   0.6553   1.0000
   1.000   0.4799   0.02448   0.01315  -0.0627   0.6479   1.0000
   1.250   0.5024   0.02480   0.01334  -0.0619   0.6405   1.0000
   1.500   0.5256   0.02504   0.01342  -0.0610   0.6347   1.0000
   1.750   0.5468   0.02556   0.01389  -0.0603   0.6264   1.0000
   2.000   0.5701   0.02579   0.01399  -0.0594   0.6210   1.0000
   2.250   0.5907   0.02640   0.01457  -0.0587   0.6133   1.0000
   2.500   0.6127   0.02678   0.01488  -0.0578   0.6071   1.0000
   2.750   0.6355   0.02710   0.01512  -0.0568   0.6018   1.0000
   3.000   0.6542   0.02786   0.01590  -0.0560   0.5939   1.0000
   3.250   0.6771   0.02818   0.01615  -0.0550   0.5888   1.0000
   3.500   0.6959   0.02891   0.01691  -0.0541   0.5820   1.0000
   3.750   0.7156   0.02951   0.01751  -0.0531   0.5755   1.0000
   4.000   0.7396   0.02973   0.01768  -0.0521   0.5712   1.0000
   4.250   0.7535   0.03086   0.01891  -0.0509   0.5631   1.0000
   4.500   0.7750   0.03128   0.01933  -0.0499   0.5576   1.0000
   4.750   0.7943   0.03191   0.01997  -0.0488   0.5518   1.0000
   5.000   0.8090   0.03288   0.02102  -0.0474   0.5443   1.0000
   5.250   0.8336   0.03303   0.02117  -0.0464   0.5398   1.0000
   5.500   0.8426   0.03441   0.02266  -0.0447   0.5312   1.0000
   5.750   0.8644   0.03475   0.02303  -0.0436   0.5257   1.0000
   6.000   0.8781   0.03573   0.02410  -0.0420   0.5187   1.0000
   6.250   0.8930   0.03658   0.02503  -0.0405   0.5116   1.0000
   6.500   0.9213   0.03646   0.02493  -0.0398   0.5076   1.0000
   6.750   0.9193   0.03856   0.02717  -0.0372   0.4977   1.0000
   7.000   0.9458   0.03858   0.02727  -0.0364   0.4932   1.0000
   7.250   0.9431   0.04076   0.02958  -0.0339   0.4840   1.0000
   7.500   0.9658   0.04105   0.02996  -0.0329   0.4788   1.0000
   7.750   0.9661   0.04304   0.03205  -0.0306   0.4704   1.0000
   8.000   0.9814   0.04388   0.03300  -0.0292   0.4640   1.0000
   8.250   1.0163   0.04332   0.03256  -0.0289   0.4606   1.0000
   8.500   0.9909   0.04722   0.03656  -0.0254   0.4486   1.0000
   8.750   1.0269   0.04652   0.03601  -0.0251   0.4452   1.0000
   9.000   0.9904   0.05129   0.04082  -0.0213   0.4324   1.0000
   9.250   1.0055   0.05222   0.04186  -0.0201   0.4264   1.0000
   9.500   0.9915   0.05591   0.04562  -0.0186   0.4156   1.0000
   9.750   1.0269   0.05479   0.04469  -0.0175   0.4121   1.0000
  10.000   1.0032   0.05960   0.04956  -0.0163   0.3987   1.0000
  10.500   1.0157   0.06278   0.05295  -0.0140   0.3794   1.0000
  10.750   1.0124   0.06558   0.05585  -0.0133   0.3677   1.0000
  11.250   1.0150   0.07047   0.06097  -0.0119   0.3480   1.0000
  11.500   1.0137   0.07340   0.06404  -0.0115   0.3376   1.0000
  12.000   1.0346   0.07586   0.06682  -0.0098   0.3212   1.0000
  12.250   1.0182   0.08109   0.07212  -0.0103   0.3083   1.0000
  12.500   1.0092   0.08524   0.07637  -0.0106   0.2962   1.0000
  12.750   1.0180   0.08626   0.07755  -0.0097   0.2849   1.0000
  13.000   1.0435   0.08365   0.07513  -0.0075   0.2711   1.0000
  13.250   1.0642   0.08161   0.07326  -0.0056   0.2523   1.0000
  13.500   1.0915   0.07869   0.07037  -0.0034   0.2303   1.0000
  13.750   1.0845   0.08222   0.07397  -0.0037   0.2114   1.0000
  14.000   1.0844   0.08461   0.07636  -0.0036   0.1889   1.0000
  14.250   1.0798   0.08797   0.07969  -0.0039   0.1658   1.0000
  14.500   1.0781   0.09071   0.08222  -0.0039   0.1416   1.0000
  14.750   1.0723   0.09429   0.08553  -0.0043   0.1229   1.0000
  15.000   1.0651   0.09833   0.08938  -0.0049   0.1086   1.0000
  15.250   1.0590   0.10243   0.09336  -0.0055   0.0970   1.0000
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