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MH 45 9.85% (mh45-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 45 9.85% (mh45-il)
Reynolds number: 50,000
Max Cl/Cd: 32.68 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh45-il-50000-n5.txt
Download as CSV file: xf-mh45-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 45  9.85%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5602   0.09554   0.08916   0.0021   1.0000   0.0351
  -9.000  -0.5622   0.09008   0.08378  -0.0014   1.0000   0.0349
  -8.750  -0.5643   0.08456   0.07833  -0.0052   1.0000   0.0345
  -8.500  -0.5684   0.07827   0.07208  -0.0103   1.0000   0.0339
  -8.250  -0.5779   0.07205   0.06589  -0.0155   1.0000   0.0333
  -8.000  -0.5853   0.06635   0.06009  -0.0193   1.0000   0.0328
  -7.750  -0.5891   0.06102   0.05458  -0.0222   1.0000   0.0324
  -7.500  -0.5892   0.05589   0.04917  -0.0242   1.0000   0.0325
  -7.250  -0.5842   0.05125   0.04416  -0.0254   1.0000   0.0329
  -7.000  -0.5749   0.04700   0.03946  -0.0260   1.0000   0.0337
  -6.750  -0.5615   0.04315   0.03510  -0.0261   1.0000   0.0347
  -6.500  -0.5448   0.03970   0.03105  -0.0259   1.0000   0.0360
  -6.250  -0.5249   0.03673   0.02751  -0.0254   1.0000   0.0369
  -6.000  -0.5045   0.03378   0.02439  -0.0250   1.0000   0.0381
  -5.750  -0.4825   0.03152   0.02192  -0.0245   1.0000   0.0399
  -5.500  -0.4602   0.02966   0.01981  -0.0238   1.0000   0.0439
  -5.250  -0.4378   0.02791   0.01779  -0.0229   1.0000   0.0488
  -5.000  -0.4187   0.02632   0.01619  -0.0218   1.0000   0.0538
  -4.750  -0.4011   0.02496   0.01472  -0.0202   1.0000   0.0626
  -4.500  -0.3862   0.02372   0.01345  -0.0184   1.0000   0.0749
  -4.250  -0.3717   0.02247   0.01229  -0.0166   1.0000   0.0989
  -4.000  -0.3558   0.02095   0.01128  -0.0154   1.0000   0.1681
  -3.750  -0.3223   0.01989   0.01075  -0.0176   0.9858   0.3032
  -3.500  -0.2876   0.01934   0.01050  -0.0194   0.9729   0.4048
  -3.250  -0.2517   0.01887   0.01011  -0.0209   0.9608   0.4753
  -3.000  -0.2169   0.01844   0.00978  -0.0221   0.9489   0.5414
  -2.750  -0.1831   0.01807   0.00950  -0.0227   0.9372   0.6123
  -2.500  -0.1489   0.01775   0.00933  -0.0230   0.9261   0.6912
  -2.250  -0.1083   0.01753   0.00920  -0.0240   0.9161   0.7796
  -2.000  -0.0526   0.01742   0.00898  -0.0280   0.9068   0.8678
  -1.750   0.0127   0.01735   0.00863  -0.0344   0.8980   0.9348
  -1.500   0.0741   0.01725   0.00821  -0.0407   0.8873   0.9856
  -1.250   0.1082   0.01728   0.00798  -0.0423   0.8728   1.0000
  -1.000   0.1293   0.01742   0.00792  -0.0413   0.8572   1.0000
  -0.750   0.1500   0.01759   0.00789  -0.0401   0.8419   1.0000
  -0.500   0.1708   0.01778   0.00790  -0.0389   0.8271   1.0000
  -0.250   0.1918   0.01797   0.00794  -0.0375   0.8127   1.0000
   0.000   0.2130   0.01817   0.00800  -0.0362   0.7986   1.0000
   0.250   0.2344   0.01837   0.00807  -0.0348   0.7845   1.0000
   0.500   0.2560   0.01856   0.00816  -0.0335   0.7707   1.0000
   0.750   0.2778   0.01876   0.00825  -0.0321   0.7568   1.0000
   1.000   0.2999   0.01894   0.00835  -0.0307   0.7430   1.0000
   1.250   0.3221   0.01912   0.00847  -0.0294   0.7289   1.0000
   1.500   0.3447   0.01931   0.00859  -0.0282   0.7145   1.0000
   1.750   0.3674   0.01948   0.00872  -0.0269   0.7001   1.0000
   2.000   0.3904   0.01965   0.00886  -0.0257   0.6855   1.0000
   2.250   0.4135   0.01983   0.00902  -0.0245   0.6704   1.0000
   2.500   0.4370   0.02001   0.00919  -0.0234   0.6547   1.0000
   2.750   0.4606   0.02019   0.00937  -0.0223   0.6386   1.0000
   3.000   0.4842   0.02037   0.00955  -0.0212   0.6223   1.0000
   3.250   0.5080   0.02054   0.00976  -0.0201   0.6058   1.0000
   3.500   0.5317   0.02071   0.00992  -0.0190   0.5891   1.0000
   3.750   0.5556   0.02086   0.01007  -0.0178   0.5722   1.0000
   4.000   0.5795   0.02104   0.01029  -0.0167   0.5547   1.0000
   4.250   0.6034   0.02129   0.01058  -0.0157   0.5351   1.0000
   4.500   0.6272   0.02150   0.01081  -0.0146   0.5162   1.0000
   4.750   0.6511   0.02174   0.01105  -0.0135   0.4969   1.0000
   5.000   0.6747   0.02206   0.01145  -0.0126   0.4756   1.0000
   5.500   0.7214   0.02278   0.01221  -0.0106   0.4328   1.0000
   5.750   0.7445   0.02318   0.01260  -0.0096   0.4112   1.0000
   6.000   0.7672   0.02369   0.01320  -0.0088   0.3880   1.0000
   6.250   0.7895   0.02423   0.01378  -0.0079   0.3652   1.0000
   6.500   0.8114   0.02483   0.01438  -0.0069   0.3424   1.0000
   6.750   0.8327   0.02553   0.01515  -0.0061   0.3188   1.0000
   7.000   0.8536   0.02626   0.01587  -0.0052   0.2969   1.0000
   7.250   0.8738   0.02711   0.01684  -0.0044   0.2742   1.0000
   7.500   0.8935   0.02801   0.01774  -0.0035   0.2536   1.0000
   7.750   0.9125   0.02903   0.01884  -0.0026   0.2332   1.0000
   8.000   0.9309   0.03009   0.01992  -0.0017   0.2153   1.0000
   8.250   0.9487   0.03125   0.02110  -0.0008   0.1984   1.0000
   8.500   0.9660   0.03253   0.02253   0.0001   0.1827   1.0000
   8.750   0.9827   0.03388   0.02397   0.0010   0.1685   1.0000
   9.000   0.9981   0.03529   0.02546   0.0020   0.1552   1.0000
   9.250   1.0138   0.03677   0.02696   0.0030   0.1441   1.0000
   9.500   1.0272   0.03841   0.02881   0.0040   0.1328   1.0000
   9.750   1.0391   0.04022   0.03083   0.0050   0.1225   1.0000
  10.000   1.0516   0.04210   0.03281   0.0060   0.1142   1.0000
  10.250   1.0609   0.04392   0.03476   0.0070   0.1059   1.0000
  10.500   1.0667   0.04629   0.03745   0.0081   0.0987   1.0000
  10.750   1.0745   0.04829   0.03951   0.0092   0.0927   1.0000
  11.000   1.0732   0.05102   0.04251   0.0104   0.0878   1.0000
  11.250   1.0694   0.05379   0.04550   0.0111   0.0831   1.0000
  11.500   1.0767   0.05581   0.04741   0.0118   0.0785   1.0000
  11.750   1.0642   0.06008   0.05209   0.0115   0.0764   1.0000
  12.000   1.0497   0.06479   0.05711   0.0104   0.0745   1.0000
  12.250   1.0332   0.07004   0.06261   0.0085   0.0730   1.0000
  12.500   1.0124   0.07641   0.06918   0.0054   0.0723   1.0000
  12.750   0.9834   0.08487   0.07783   0.0005   0.0728   1.0000
  13.000   0.9446   0.09644   0.08953  -0.0068   0.0747   1.0000
  13.250   0.9031   0.11032   0.10337  -0.0154   0.0760   1.0000
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