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MH 121 8.76% (mh121-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 121 8.76% (mh121-il)
Reynolds number: 50,000
Max Cl/Cd: 31.95 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh121-il-50000.txt
Download as CSV file: xf-mh121-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 121  8.76%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.4349   0.09939   0.09324  -0.0211   1.0000   0.2746
  -7.250  -0.4426   0.09756   0.09136  -0.0186   1.0000   0.2886
  -7.000  -0.4513   0.09584   0.08975  -0.0157   1.0000   0.3024
  -6.750  -0.4607   0.09419   0.08821  -0.0125   1.0000   0.3161
  -6.500  -0.4683   0.09222   0.08635  -0.0092   1.0000   0.3308
  -6.250  -0.4699   0.09028   0.08449  -0.0052   1.0000   0.3561
  -6.000  -0.4609   0.08732   0.08156  -0.0019   1.0000   0.3816
  -5.750  -0.4528   0.08430   0.07858   0.0012   1.0000   0.4058
  -4.750  -0.4384   0.04952   0.04243  -0.0539   1.0000   0.1145
  -4.500  -0.4082   0.04430   0.03656  -0.0567   1.0000   0.0989
  -4.250  -0.3730   0.04038   0.03129  -0.0592   1.0000   0.0907
  -4.000  -0.3435   0.03721   0.02755  -0.0602   1.0000   0.0913
  -3.750  -0.3155   0.03401   0.02410  -0.0607   1.0000   0.0933
  -3.500  -0.2855   0.03159   0.02113  -0.0605   1.0000   0.0927
  -3.250  -0.2582   0.02937   0.01872  -0.0597   1.0000   0.0959
  -3.000  -0.2317   0.02765   0.01673  -0.0583   1.0000   0.1034
  -2.750  -0.2073   0.02595   0.01509  -0.0572   1.0000   0.1303
  -2.500  -0.1753   0.02161   0.01373  -0.0567   1.0000   0.5878
  -2.250  -0.1861   0.02198   0.01445  -0.0448   1.0000   0.7379
  -2.000  -0.1935   0.02184   0.01437  -0.0350   1.0000   0.8119
  -1.750  -0.2025   0.02130   0.01391  -0.0253   1.0000   0.8852
  -1.500  -0.1652   0.02051   0.01279  -0.0266   1.0000   1.0000
  -1.250  -0.1321   0.02034   0.01211  -0.0307   1.0000   1.0000
  -1.000  -0.0954   0.02040   0.01155  -0.0350   1.0000   1.0000
  -0.750  -0.0604   0.02059   0.01130  -0.0384   1.0000   1.0000
  -0.500  -0.0281   0.02085   0.01117  -0.0410   1.0000   1.0000
  -0.250   0.0015   0.02116   0.01115  -0.0428   1.0000   1.0000
   0.000   0.0292   0.02150   0.01122  -0.0440   1.0000   1.0000
   0.250   0.0555   0.02188   0.01135  -0.0449   1.0000   1.0000
   0.500   0.0807   0.02228   0.01145  -0.0455   1.0000   1.0000
   0.750   0.1051   0.02271   0.01171  -0.0459   1.0000   1.0000
   1.000   0.1289   0.02317   0.01204  -0.0463   1.0000   1.0000
   1.250   0.1521   0.02366   0.01242  -0.0465   1.0000   1.0000
   1.500   0.1749   0.02418   0.01286  -0.0467   1.0000   1.0000
   1.750   0.1972   0.02472   0.01336  -0.0468   1.0000   1.0000
   2.000   0.2191   0.02531   0.01392  -0.0468   1.0000   1.0000
   2.250   0.2406   0.02593   0.01452  -0.0469   1.0000   1.0000
   2.500   0.2616   0.02659   0.01519  -0.0469   1.0000   1.0000
   2.750   0.2822   0.02729   0.01591  -0.0469   1.0000   1.0000
   3.000   0.3024   0.02804   0.01671  -0.0469   1.0000   1.0000
   3.250   0.3221   0.02884   0.01758  -0.0469   1.0000   1.0000
   3.500   0.3413   0.02970   0.01860  -0.0469   1.0000   1.0000
   3.750   0.3600   0.03063   0.01963  -0.0469   1.0000   1.0000
   4.000   0.3781   0.03162   0.02074  -0.0470   1.0000   1.0000
   4.250   0.3956   0.03270   0.02195  -0.0471   1.0000   1.0000
   4.500   0.4124   0.03386   0.02326  -0.0472   1.0000   1.0000
   4.750   0.4374   0.03541   0.02502  -0.0492   0.9951   1.0000
   5.000   0.5067   0.03783   0.02805  -0.0589   0.9606   1.0000
   5.250   0.5705   0.03932   0.03007  -0.0664   0.9242   1.0000
   5.500   0.6536   0.03955   0.03106  -0.0745   0.8753   1.0000
   5.750   0.8380   0.02623   0.01650  -0.0682   0.2382   1.0000
   6.250   0.9420   0.03630   0.02528  -0.0726   0.0895   1.0000
   6.500   0.9746   0.04059   0.02961  -0.0729   0.0738   1.0000
   6.750   0.9974   0.04353   0.03331  -0.0708   0.0689   1.0000
   7.000   1.0200   0.04771   0.03806  -0.0690   0.0689   1.0000
   7.250   1.0371   0.05207   0.04295  -0.0667   0.0704   1.0000
   7.500   1.0516   0.05685   0.04810  -0.0647   0.0726   1.0000
   7.750   1.0572   0.06078   0.05284  -0.0609   0.0781   1.0000
   8.000   1.0602   0.06586   0.05840  -0.0582   0.0838   1.0000
   8.250   1.0572   0.07067   0.06380  -0.0550   0.0926   1.0000
   8.500   1.0530   0.07605   0.06960  -0.0526   0.1039   1.0000
   8.750   1.0518   0.08315   0.07707  -0.0515   0.1272   1.0000
   9.000   1.0181   0.08684   0.08106  -0.0491   0.1305   1.0000
   9.250   0.9924   0.09214   0.08652  -0.0485   0.1430   1.0000
   9.500   0.9638   0.09830   0.09278  -0.0504   0.1556   1.0000
   9.750   0.8821   0.09734   0.09209  -0.0400   0.1250   1.0000
  10.000   0.8501   0.10344   0.09824  -0.0426   0.1247   1.0000
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