Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

MH 60 10.08% (mh60-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 60 10.08% (mh60-il)
Reynolds number: 50,000
Max Cl/Cd: 32.89 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh60-il-50000-n5.txt
Download as CSV file: xf-mh60-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 60  10.08%                                   
  
 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  -0.5403   0.09566   0.08939  -0.0011   1.0000   0.0360
  -9.000  -0.5457   0.08912   0.08294  -0.0058   1.0000   0.0350
  -8.750  -0.5602   0.07873   0.07253  -0.0162   1.0000   0.0329
  -8.500  -0.5678   0.07351   0.06733  -0.0202   1.0000   0.0327
  -8.250  -0.5748   0.06857   0.06232  -0.0230   1.0000   0.0325
  -8.000  -0.5786   0.06373   0.05735  -0.0254   1.0000   0.0323
  -7.750  -0.5792   0.05903   0.05245  -0.0272   1.0000   0.0321
  -7.500  -0.5768   0.05439   0.04751  -0.0285   1.0000   0.0321
  -7.250  -0.5703   0.05002   0.04276  -0.0292   1.0000   0.0321
  -7.000  -0.5603   0.04588   0.03817  -0.0294   1.0000   0.0323
  -6.750  -0.5465   0.04226   0.03402  -0.0293   1.0000   0.0328
  -6.500  -0.5312   0.03900   0.03051  -0.0291   1.0000   0.0344
  -6.250  -0.5132   0.03669   0.02801  -0.0288   1.0000   0.0371
  -6.000  -0.4940   0.03428   0.02519  -0.0281   1.0000   0.0397
  -5.750  -0.4741   0.03188   0.02238  -0.0270   1.0000   0.0419
  -5.500  -0.4546   0.02992   0.02006  -0.0255   1.0000   0.0442
  -5.250  -0.4405   0.02832   0.01850  -0.0239   1.0000   0.0491
  -5.000  -0.4257   0.02702   0.01693  -0.0217   1.0000   0.0556
  -4.750  -0.4130   0.02569   0.01563  -0.0196   1.0000   0.0622
  -4.500  -0.3994   0.02452   0.01439  -0.0175   1.0000   0.0748
  -4.250  -0.3677   0.02289   0.01282  -0.0188   0.9896   0.1074
  -4.000  -0.3318   0.02111   0.01157  -0.0214   0.9795   0.2057
  -3.750  -0.2972   0.02021   0.01112  -0.0235   0.9691   0.3256
  -3.500  -0.2638   0.01966   0.01080  -0.0249   0.9585   0.4182
  -3.250  -0.2314   0.01922   0.01049  -0.0256   0.9477   0.4938
  -3.000  -0.1992   0.01882   0.01019  -0.0261   0.9373   0.5657
  -2.750  -0.1661   0.01848   0.01000  -0.0264   0.9277   0.6413
  -2.500  -0.1331   0.01822   0.00988  -0.0263   0.9175   0.7220
  -2.250  -0.0889   0.01807   0.00975  -0.0279   0.9088   0.8097
  -2.000  -0.0261   0.01801   0.00947  -0.0334   0.9021   0.8886
  -1.750   0.0358   0.01797   0.00913  -0.0394   0.8931   0.9453
  -1.500   0.0966   0.01785   0.00869  -0.0458   0.8836   0.9906
  -1.250   0.1265   0.01790   0.00850  -0.0467   0.8700   1.0000
  -1.000   0.1468   0.01804   0.00845  -0.0456   0.8554   1.0000
  -0.750   0.1672   0.01820   0.00841  -0.0444   0.8414   1.0000
  -0.500   0.1877   0.01837   0.00842  -0.0431   0.8276   1.0000
  -0.250   0.2084   0.01855   0.00845  -0.0418   0.8142   1.0000
   0.000   0.2293   0.01873   0.00849  -0.0403   0.8009   1.0000
   0.250   0.2504   0.01890   0.00853  -0.0389   0.7879   1.0000
   0.500   0.2717   0.01909   0.00862  -0.0375   0.7744   1.0000
   0.750   0.2931   0.01927   0.00871  -0.0361   0.7607   1.0000
   1.000   0.3149   0.01945   0.00882  -0.0348   0.7470   1.0000
   1.250   0.3367   0.01963   0.00894  -0.0334   0.7332   1.0000
   1.500   0.3589   0.01980   0.00905  -0.0321   0.7193   1.0000
   1.750   0.3813   0.01997   0.00917  -0.0308   0.7052   1.0000
   2.000   0.4040   0.02012   0.00929  -0.0295   0.6909   1.0000
   2.250   0.4269   0.02027   0.00943  -0.0283   0.6764   1.0000
   2.500   0.4500   0.02041   0.00955  -0.0270   0.6616   1.0000
   2.750   0.4732   0.02054   0.00966  -0.0257   0.6467   1.0000
   3.000   0.4965   0.02066   0.00977  -0.0244   0.6315   1.0000
   3.250   0.5199   0.02085   0.01001  -0.0234   0.6145   1.0000
   3.500   0.5434   0.02103   0.01021  -0.0223   0.5973   1.0000
   3.750   0.5670   0.02118   0.01038  -0.0211   0.5803   1.0000
   4.000   0.5907   0.02133   0.01053  -0.0199   0.5632   1.0000
   4.250   0.6145   0.02148   0.01072  -0.0187   0.5459   1.0000
   4.500   0.6381   0.02176   0.01105  -0.0178   0.5262   1.0000
   4.750   0.6617   0.02198   0.01129  -0.0167   0.5073   1.0000
   5.000   0.6853   0.02224   0.01155  -0.0156   0.4883   1.0000
   5.250   0.7086   0.02261   0.01200  -0.0147   0.4676   1.0000
   5.500   0.7320   0.02293   0.01232  -0.0136   0.4481   1.0000
   5.750   0.7548   0.02341   0.01286  -0.0127   0.4268   1.0000
   6.000   0.7776   0.02386   0.01332  -0.0117   0.4065   1.0000
   6.250   0.7999   0.02442   0.01398  -0.0108   0.3854   1.0000
   6.500   0.8220   0.02499   0.01459  -0.0099   0.3649   1.0000
   6.750   0.8437   0.02565   0.01530  -0.0090   0.3445   1.0000
   7.000   0.8648   0.02636   0.01608  -0.0081   0.3240   1.0000
   7.250   0.8857   0.02710   0.01684  -0.0072   0.3049   1.0000
   7.500   0.9056   0.02796   0.01784  -0.0063   0.2847   1.0000
   7.750   0.9253   0.02884   0.01883  -0.0054   0.2664   1.0000
   8.000   0.9442   0.02978   0.01980  -0.0044   0.2485   1.0000
   8.250   0.9622   0.03085   0.02102  -0.0035   0.2307   1.0000
   8.500   0.9793   0.03196   0.02224  -0.0025   0.2137   1.0000
   8.750   0.9956   0.03314   0.02351  -0.0014   0.1980   1.0000
   9.000   1.0106   0.03439   0.02484  -0.0003   0.1828   1.0000
   9.500   1.0362   0.03720   0.02790   0.0020   0.1545   1.0000
   9.750   1.0467   0.03882   0.02965   0.0032   0.1416   1.0000
  10.000   1.0544   0.04057   0.03154   0.0044   0.1295   1.0000
  10.250   1.0600   0.04247   0.03358   0.0057   0.1185   1.0000
  10.500   1.0636   0.04443   0.03561   0.0072   0.1093   1.0000
  10.750   1.0637   0.04645   0.03768   0.0085   0.1010   1.0000
  11.000   1.0625   0.04913   0.04060   0.0094   0.0934   1.0000
  11.250   1.0641   0.05134   0.04271   0.0102   0.0869   1.0000
  11.500   1.0579   0.05486   0.04661   0.0103   0.0812   1.0000
  11.750   1.0554   0.05769   0.04947   0.0102   0.0759   1.0000
  12.000   1.0500   0.06150   0.05347   0.0098   0.0720   1.0000
  12.250   1.0399   0.06610   0.05836   0.0086   0.0688   1.0000
  12.500   1.0312   0.07046   0.06287   0.0072   0.0658   1.0000
  12.750   1.0300   0.07363   0.06595   0.0065   0.0620   1.0000
  13.000   1.0128   0.08003   0.07264   0.0035   0.0610   1.0000
  13.250   0.9932   0.08727   0.08012  -0.0003   0.0605   1.0000
  13.500   0.9709   0.09556   0.08861  -0.0049   0.0605   1.0000
  13.750   0.9458   0.10516   0.09834  -0.0104   0.0611   1.0000
  14.000   0.9197   0.11581   0.10905  -0.0164   0.0618   1.0000
<< Back to MH 60 10.08% (mh60-il)

Polar data table (+)

Polar graphs


<< Back to MH 60 10.08% (mh60-il)