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MH 27 11.99% (mh27-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 27 11.99% (mh27-il)
Reynolds number: 100,000
Max Cl/Cd: 46.4 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh27-il-100000-n5.txt
Download as CSV file: xf-mh27-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 27  11.99%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4349   0.09620   0.09172  -0.0356   1.0000   0.0153
  -9.750  -0.4468   0.09091   0.08648  -0.0366   1.0000   0.0151
  -9.500  -0.4636   0.08418   0.07980  -0.0385   1.0000   0.0144
  -9.250  -0.4942   0.07147   0.06702  -0.0449   1.0000   0.0129
  -8.750  -0.6148   0.07281   0.06793  -0.0402   1.0000   0.0127
  -8.500  -0.6398   0.07051   0.06557  -0.0353   1.0000   0.0126
  -8.250  -0.6628   0.06803   0.06301  -0.0300   1.0000   0.0126
  -8.000  -0.6783   0.06542   0.06029  -0.0257   1.0000   0.0125
  -7.750  -0.6918   0.06253   0.05728  -0.0213   1.0000   0.0124
  -7.500  -0.7053   0.05905   0.05356  -0.0166   1.0000   0.0124
  -7.250  -0.7118   0.05634   0.05068  -0.0126   1.0000   0.0122
  -7.000  -0.7157   0.05284   0.04687  -0.0088   0.9992   0.0122
  -6.750  -0.7087   0.04904   0.04262  -0.0069   0.9958   0.0121
  -6.500  -0.6997   0.04544   0.03856  -0.0047   0.9927   0.0121
  -6.250  -0.6880   0.04231   0.03497  -0.0026   0.9894   0.0121
  -6.000  -0.6721   0.03955   0.03162  -0.0006   0.9863   0.0129
  -5.750  -0.6552   0.03704   0.02882   0.0003   0.9838   0.0142
  -5.500  -0.6364   0.03506   0.02648   0.0018   0.9807   0.0145
  -5.250  -0.6154   0.03353   0.02466   0.0028   0.9776   0.0165
  -5.000  -0.5900   0.03164   0.02240   0.0034   0.9751   0.0169
  -4.750  -0.5617   0.02980   0.02021   0.0037   0.9731   0.0178
  -4.500  -0.5322   0.02834   0.01852   0.0035   0.9713   0.0188
  -4.250  -0.5099   0.02718   0.01713   0.0047   0.9678   0.0197
  -4.000  -0.4884   0.02589   0.01576   0.0059   0.9643   0.0219
  -3.750  -0.4627   0.02522   0.01501   0.0060   0.9610   0.0282
  -3.500  -0.4365   0.02434   0.01403   0.0062   0.9584   0.0346
  -3.250  -0.4179   0.02342   0.01319   0.0081   0.9538   0.0573
  -3.000  -0.3982   0.02213   0.01258   0.0092   0.9498   0.1671
  -2.750  -0.2836   0.02113   0.01458  -0.0065   0.9612   0.8529
  -2.500  -0.2495   0.02197   0.01516  -0.0070   0.9587   0.8996
  -2.250  -0.2004   0.02288   0.01577  -0.0107   0.9579   0.9282
  -2.000  -0.1354   0.02372   0.01631  -0.0180   0.9585   0.9522
  -1.750  -0.0778   0.02413   0.01648  -0.0243   0.9582   0.9670
  -1.500  -0.0323   0.02417   0.01635  -0.0285   0.9556   0.9752
  -1.250   0.0103   0.02422   0.01624  -0.0322   0.9524   0.9834
  -1.000   0.0590   0.02414   0.01603  -0.0372   0.9498   0.9894
  -0.750   0.1066   0.02412   0.01590  -0.0420   0.9474   0.9953
  -0.500   0.1552   0.02406   0.01575  -0.0471   0.9453   1.0000
  -0.250   0.1776   0.02392   0.01556  -0.0466   0.9376   1.0000
   0.000   0.2117   0.02383   0.01543  -0.0485   0.9326   1.0000
   0.250   0.2354   0.02368   0.01526  -0.0482   0.9245   1.0000
   0.500   0.2698   0.02355   0.01510  -0.0500   0.9192   1.0000
   0.750   0.2926   0.02338   0.01494  -0.0494   0.9103   1.0000
   1.000   0.3296   0.02318   0.01474  -0.0516   0.9051   1.0000
   1.250   0.3506   0.02297   0.01457  -0.0505   0.8948   1.0000
   1.500   0.3768   0.02273   0.01436  -0.0504   0.8858   1.0000
   1.750   0.4108   0.02241   0.01408  -0.0518   0.8787   1.0000
   2.000   0.4318   0.02215   0.01387  -0.0505   0.8671   1.0000
   2.250   0.4542   0.02186   0.01364  -0.0495   0.8556   1.0000
   2.500   0.4777   0.02154   0.01342  -0.0486   0.8436   1.0000
   2.750   0.5012   0.02119   0.01315  -0.0476   0.8311   1.0000
   3.000   0.5244   0.02081   0.01285  -0.0465   0.8176   1.0000
   3.250   0.5470   0.02042   0.01258  -0.0451   0.8033   1.0000
   3.500   0.5723   0.01998   0.01223  -0.0443   0.7874   1.0000
   3.750   0.6037   0.01943   0.01178  -0.0445   0.7704   1.0000
   4.000   0.6334   0.01897   0.01141  -0.0443   0.7471   1.0000
   4.250   0.6801   0.01824   0.01078  -0.0473   0.7169   1.0000
   4.500   0.7547   0.01749   0.00999  -0.0558   0.6593   1.0000
   4.750   0.8031   0.01745   0.00974  -0.0596   0.5868   1.0000
   5.000   0.8269   0.01782   0.00990  -0.0587   0.5228   1.0000
   5.250   0.8411   0.01833   0.01018  -0.0560   0.4654   1.0000
   5.500   0.8515   0.01890   0.01053  -0.0527   0.4132   1.0000
   5.750   0.8600   0.01951   0.01094  -0.0491   0.3654   1.0000
   6.000   0.8681   0.02011   0.01138  -0.0454   0.3215   1.0000
   6.250   0.8752   0.02076   0.01186  -0.0417   0.2792   1.0000
   6.500   0.8819   0.02143   0.01238  -0.0379   0.2409   1.0000
   6.750   0.8878   0.02208   0.01291  -0.0340   0.2044   1.0000
   7.000   0.8934   0.02276   0.01346  -0.0301   0.1734   1.0000
   7.250   0.8986   0.02349   0.01407  -0.0262   0.1446   1.0000
   7.500   0.9045   0.02423   0.01479  -0.0224   0.1200   1.0000
   7.750   0.9100   0.02503   0.01553  -0.0186   0.0977   1.0000
   8.000   0.9149   0.02587   0.01632  -0.0147   0.0814   1.0000
   8.250   0.9195   0.02676   0.01720  -0.0108   0.0684   1.0000
   8.500   0.9243   0.02765   0.01811  -0.0070   0.0579   1.0000
   8.750   0.9270   0.02868   0.01917  -0.0029   0.0518   1.0000
   9.000   0.9309   0.02970   0.02032   0.0011   0.0464   1.0000
   9.250   0.9318   0.03092   0.02155   0.0052   0.0424   1.0000
   9.500   0.9382   0.03195   0.02277   0.0086   0.0380   1.0000
   9.750   0.9427   0.03305   0.02396   0.0120   0.0341   1.0000
  10.000   0.9447   0.03455   0.02550   0.0156   0.0319   1.0000
  10.250   0.9519   0.03614   0.02728   0.0186   0.0295   1.0000
  10.500   0.9577   0.03745   0.02880   0.0216   0.0262   1.0000
  10.750   0.9612   0.03880   0.03034   0.0247   0.0242   1.0000
  11.000   0.9625   0.04071   0.03232   0.0278   0.0224   1.0000
  11.250   0.9662   0.04303   0.03485   0.0306   0.0211   1.0000
  11.500   0.9663   0.04489   0.03705   0.0339   0.0191   1.0000
  11.750   0.9646   0.04686   0.03927   0.0370   0.0179   1.0000
  12.000   0.9599   0.04882   0.04143   0.0400   0.0166   1.0000
  12.250   0.9532   0.05134   0.04416   0.0430   0.0159   1.0000
  12.500   0.9445   0.05390   0.04689   0.0456   0.0153   1.0000
  12.750   0.9346   0.05681   0.05000   0.0479   0.0150   1.0000
  13.000   0.9219   0.06005   0.05341   0.0497   0.0146   1.0000
  13.250   0.9086   0.06357   0.05715   0.0510   0.0146   1.0000
  13.500   0.8914   0.06775   0.06152   0.0517   0.0143   1.0000
  13.750   0.8754   0.07211   0.06611   0.0516   0.0144   1.0000
  14.000   0.8564   0.07721   0.07138   0.0506   0.0143   1.0000
  14.250   0.8367   0.08299   0.07736   0.0486   0.0143   1.0000
  14.500   0.8169   0.08943   0.08397   0.0456   0.0143   1.0000
  14.750   0.7866   0.09941   0.09425   0.0399   0.0152   1.0000
  15.000   0.7407   0.11517   0.11020   0.0308   0.0166   1.0000
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