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NACA M20 AIRFOIL (m20-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA M20 AIRFOIL (m20-il)
Reynolds number: 50,000
Max Cl/Cd: 26.75 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m20-il-50000-n5.txt
Download as CSV file: xf-m20-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M20 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3085   0.11422   0.10854  -0.0198   1.0000   0.0667
  -8.250  -0.3071   0.11324   0.10768  -0.0247   1.0000   0.0672
  -8.000  -0.3029   0.11249   0.10701  -0.0310   0.9837   0.0676
  -7.750  -0.2792   0.10274   0.09726  -0.0265   0.9707   0.0711
  -7.500  -0.2623   0.09895   0.09344  -0.0303   0.9421   0.0751
  -7.250  -0.2480   0.09610   0.09052  -0.0353   0.9199   0.0788
  -7.000  -0.2349   0.09496   0.08928  -0.0423   0.8992   0.0812
  -6.750  -0.2193   0.09440   0.08851  -0.0493   0.8818   0.0819
  -6.500  -0.2110   0.08787   0.08204  -0.0459   0.8706   0.0834
  -6.250  -0.2007   0.08397   0.07809  -0.0447   0.8588   0.0865
  -6.000  -0.1878   0.08130   0.07534  -0.0463   0.8467   0.0918
  -5.750  -0.1622   0.08193   0.07563  -0.0554   0.8336   0.0967
  -5.500  -0.1559   0.07602   0.06984  -0.0522   0.8241   0.0989
  -5.250  -0.1424   0.07282   0.06655  -0.0521   0.8148   0.1027
  -5.000  -0.1216   0.07069   0.06425  -0.0551   0.8045   0.1089
  -4.750  -0.0988   0.06839   0.06173  -0.0586   0.7949   0.1120
  -4.500  -0.0867   0.06476   0.05808  -0.0572   0.7870   0.1173
  -4.000  -0.0457   0.05982   0.05283  -0.0599   0.7699   0.1338
  -3.500  -0.0010   0.05514   0.04781  -0.0623   0.7534   0.1490
  -3.250   0.0223   0.05292   0.04538  -0.0635   0.7451   0.1584
  -2.750   0.0663   0.04872   0.04087  -0.0644   0.7300   0.1892
  -2.500   0.0869   0.04676   0.03877  -0.0645   0.7229   0.2172
  -2.250   0.1068   0.04469   0.03659  -0.0643   0.7152   0.2472
  -1.750   0.1948   0.04086   0.03141  -0.0684   0.7015   0.0921
  -1.500   0.2234   0.03905   0.02921  -0.0683   0.6961   0.0857
  -1.250   0.2538   0.03785   0.02757  -0.0687   0.6878   0.0807
  -1.000   0.2812   0.03656   0.02592  -0.0684   0.6822   0.0810
  -0.750   0.3080   0.03548   0.02462  -0.0686   0.6747   0.0831
  -0.500   0.3348   0.03438   0.02327  -0.0684   0.6687   0.0838
   0.000   0.3915   0.03274   0.02095  -0.0682   0.6555   0.0816
   0.250   0.4198   0.03181   0.01974  -0.0678   0.6510   0.0815
   0.500   0.4472   0.03138   0.01911  -0.0681   0.6430   0.0817
   0.750   0.4788   0.03069   0.01813  -0.0683   0.6378   0.0824
   1.000   0.5092   0.03033   0.01761  -0.0690   0.6310   0.0839
   1.250   0.5382   0.02998   0.01714  -0.0691   0.6251   0.0862
   1.500   0.5658   0.02962   0.01661  -0.0686   0.6209   0.0929
   1.750   0.5901   0.02979   0.01680  -0.0687   0.6130   0.1002
   2.000   0.6152   0.02958   0.01650  -0.0680   0.6083   0.1075
   2.250   0.6387   0.02965   0.01654  -0.0675   0.6025   0.1153
   2.500   0.6619   0.02978   0.01668  -0.0671   0.5964   0.1297
   2.750   0.6862   0.02949   0.01653  -0.0663   0.5923   0.1791
   3.000   0.7337   0.02862   0.01700  -0.0711   0.5853   1.0000
   3.250   0.7570   0.02913   0.01733  -0.0705   0.5801   1.0000
   3.500   0.7820   0.02936   0.01738  -0.0697   0.5765   1.0000
   3.750   0.8006   0.03056   0.01860  -0.0695   0.5687   1.0000
   4.000   0.8241   0.03102   0.01899  -0.0689   0.5642   1.0000
   4.250   0.8466   0.03165   0.01959  -0.0683   0.5595   1.0000
   4.500   0.8647   0.03282   0.02082  -0.0679   0.5526   1.0000
   4.750   0.8887   0.03324   0.02121  -0.0673   0.5486   1.0000
   5.000   0.9063   0.03445   0.02252  -0.0668   0.5424   1.0000
   5.250   0.9251   0.03549   0.02362  -0.0663   0.5365   1.0000
   5.500   0.9498   0.03583   0.02399  -0.0656   0.5330   1.0000
   5.750   0.9605   0.03778   0.02607  -0.0650   0.5253   1.0000
   6.000   0.9809   0.03860   0.02700  -0.0644   0.5204   1.0000
   6.250   1.0070   0.03881   0.02727  -0.0637   0.5173   1.0000
   6.500   1.0084   0.04164   0.03028  -0.0629   0.5079   1.0000
   6.750   1.0321   0.04210   0.03085  -0.0622   0.5041   1.0000
   7.000   1.0326   0.04493   0.03384  -0.0613   0.4953   1.0000
   7.250   1.0522   0.04577   0.03486  -0.0605   0.4905   1.0000
   7.500   1.0723   0.04657   0.03580  -0.0597   0.4860   1.0000
   7.750   1.0673   0.04982   0.03920  -0.0586   0.4762   1.0000
   8.250   1.0815   0.05369   0.04336  -0.0565   0.4610   1.0000
   8.500   1.1096   0.05335   0.04329  -0.0554   0.4569   1.0000
   8.750   1.0969   0.05715   0.04718  -0.0543   0.4453   1.0000
   9.000   1.0817   0.06161   0.05173  -0.0537   0.4333   1.0000
   9.250   1.1203   0.05879   0.04919  -0.0513   0.4262   1.0000
   9.500   1.1849   0.04838   0.03905  -0.0452   0.3937   1.0000
   9.750   1.2000   0.04709   0.03794  -0.0425   0.3688   1.0000
  10.000   1.1886   0.05056   0.04157  -0.0418   0.3526   1.0000
  10.250   1.1762   0.05444   0.04560  -0.0414   0.3343   1.0000
  10.500   1.1669   0.05779   0.04906  -0.0410   0.3065   1.0000
  10.750   1.1760   0.05671   0.04696  -0.0375   0.1780   1.0000
  11.000   1.1545   0.06173   0.05142  -0.0370   0.1050   1.0000
  11.250   1.1339   0.06713   0.05646  -0.0372   0.0864   1.0000
  11.500   1.1188   0.07210   0.06129  -0.0373   0.0744   1.0000
  11.750   1.1076   0.07668   0.06585  -0.0375   0.0660   1.0000
  12.000   1.0993   0.08107   0.07027  -0.0378   0.0595   1.0000
  12.250   1.0924   0.08535   0.07458  -0.0381   0.0552   1.0000
  12.500   1.0880   0.08935   0.07867  -0.0385   0.0517   1.0000
  12.750   1.0841   0.09331   0.08271  -0.0388   0.0493   1.0000
  13.000   1.0804   0.09723   0.08668  -0.0392   0.0475   1.0000
  13.250   1.0791   0.10072   0.09022  -0.0393   0.0459   1.0000
  13.500   1.0812   0.10371   0.09335  -0.0392   0.0439   1.0000
  13.750   1.0840   0.10653   0.09632  -0.0391   0.0417   1.0000
  14.000   1.0873   0.10918   0.09903  -0.0388   0.0396   1.0000
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