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MH 106 13.07% (mh106-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 106 13.07% (mh106-il)
Reynolds number: 50,000
Max Cl/Cd: 14.87 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh106-il-50000.txt
Download as CSV file: xf-mh106-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 106  13.07%                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6387   0.10008   0.09365  -0.0076   1.0000   0.1053
 -10.500  -0.6228   0.09812   0.09173  -0.0053   1.0000   0.1088
 -10.250  -0.7104   0.07965   0.07319  -0.0227   1.0000   0.0916
 -10.000  -0.7225   0.07463   0.06814  -0.0239   1.0000   0.0905
  -9.750  -0.7411   0.07006   0.06351  -0.0240   1.0000   0.0894
  -9.500  -0.7595   0.06569   0.05899  -0.0232   1.0000   0.0880
  -9.250  -0.7738   0.06127   0.05432  -0.0221   1.0000   0.0867
  -9.000  -0.7835   0.05695   0.04968  -0.0207   1.0000   0.0861
  -8.750  -0.7866   0.05295   0.04530  -0.0190   1.0000   0.0862
  -8.500  -0.7843   0.04923   0.04118  -0.0172   1.0000   0.0870
  -8.250  -0.7775   0.04580   0.03729  -0.0153   1.0000   0.0887
  -8.000  -0.7666   0.04253   0.03351  -0.0134   1.0000   0.0906
  -7.750  -0.7505   0.03929   0.02979  -0.0117   1.0000   0.0930
  -7.500  -0.7271   0.03633   0.02687  -0.0109   1.0000   0.0989
  -7.250  -0.7055   0.03377   0.02416  -0.0097   1.0000   0.1087
  -7.000  -0.6827   0.03133   0.02178  -0.0085   1.0000   0.1234
  -6.750  -0.6638   0.02912   0.01970  -0.0067   1.0000   0.1490
  -6.500  -0.6528   0.02698   0.01807  -0.0038   1.0000   0.2019
  -6.250  -0.6552   0.02567   0.01768   0.0016   1.0000   0.3059
  -6.000  -0.6496   0.02596   0.01833   0.0067   1.0000   0.3821
  -5.750  -0.6362   0.02636   0.01888   0.0106   1.0000   0.4331
  -5.500  -0.6192   0.02670   0.01938   0.0142   1.0000   0.4759
  -5.250  -0.6036   0.02647   0.01914   0.0174   1.0000   0.5105
  -5.000  -0.5844   0.02612   0.01880   0.0200   1.0000   0.5382
  -4.750  -0.5661   0.02561   0.01832   0.0223   1.0000   0.5619
  -4.500  -0.5536   0.02490   0.01754   0.0248   1.0000   0.5850
  -4.250  -0.5389   0.02446   0.01715   0.0273   1.0000   0.6055
  -4.000  -0.5314   0.02396   0.01662   0.0303   1.0000   0.6267
  -3.750  -0.5242   0.02361   0.01628   0.0331   1.0000   0.6473
  -3.500  -0.5169   0.02335   0.01600   0.0357   1.0000   0.6696
  -3.250  -0.5083   0.02319   0.01584   0.0379   1.0000   0.6934
  -3.000  -0.4764   0.02330   0.01592   0.0364   0.9909   0.7256
  -2.750  -0.4045   0.02378   0.01629   0.0289   0.9679   0.7690
  -2.500  -0.3248   0.02443   0.01675   0.0208   0.9460   0.8111
  -2.250  -0.2158   0.02523   0.01725   0.0080   0.9286   0.8517
  -2.000  -0.0776   0.02567   0.01732  -0.0099   0.9118   0.8834
  -1.750   0.0270   0.02548   0.01685  -0.0231   0.8883   0.9135
  -1.500   0.1075   0.02506   0.01618  -0.0327   0.8634   0.9429
  -1.250   0.1783   0.02447   0.01537  -0.0412   0.8387   0.9724
  -1.000   0.2458   0.02363   0.01435  -0.0503   0.8154   1.0000
  -0.750   0.2582   0.02365   0.01427  -0.0495   0.7981   1.0000
  -0.500   0.2714   0.02376   0.01429  -0.0488   0.7827   1.0000
  -0.250   0.2853   0.02395   0.01441  -0.0480   0.7686   1.0000
   0.000   0.3004   0.02423   0.01462  -0.0473   0.7554   1.0000
   0.250   0.3163   0.02459   0.01492  -0.0466   0.7436   1.0000
   0.500   0.3321   0.02495   0.01520  -0.0454   0.7329   1.0000
   0.750   0.3483   0.02545   0.01569  -0.0447   0.7217   1.0000
   1.000   0.3643   0.02610   0.01632  -0.0440   0.7111   1.0000
   1.250   0.3806   0.02668   0.01686  -0.0428   0.7019   1.0000
   1.500   0.3966   0.02739   0.01755  -0.0418   0.6921   1.0000
   1.750   0.4119   0.02830   0.01850  -0.0411   0.6827   1.0000
   2.000   0.4293   0.02888   0.01902  -0.0394   0.6747   1.0000
   2.250   0.4427   0.03007   0.02026  -0.0389   0.6646   1.0000
   2.500   0.4574   0.03107   0.02127  -0.0377   0.6560   1.0000
   2.750   0.4733   0.03196   0.02217  -0.0363   0.6473   1.0000
   3.000   0.4839   0.03341   0.02368  -0.0353   0.6380   1.0000
   3.250   0.5043   0.03400   0.02424  -0.0336   0.6302   1.0000
   3.500   0.5100   0.03585   0.02617  -0.0326   0.6201   1.0000
   3.750   0.5214   0.03723   0.02759  -0.0312   0.6109   1.0000
   4.000   0.5391   0.03817   0.02856  -0.0296   0.6021   1.0000
   4.250   0.5409   0.04029   0.03074  -0.0282   0.5917   1.0000
   4.500   0.5536   0.04168   0.03216  -0.0267   0.5823   1.0000
   4.750   0.5729   0.04255   0.03308  -0.0250   0.5722   1.0000
   5.000   0.5671   0.04525   0.03581  -0.0235   0.5613   1.0000
   5.250   0.5731   0.04714   0.03774  -0.0219   0.5506   1.0000
   5.500   0.5946   0.04799   0.03868  -0.0202   0.5397   1.0000
   5.750   0.6108   0.04913   0.03990  -0.0185   0.5276   1.0000
   6.000   0.5957   0.05260   0.04337  -0.0171   0.5161   1.0000
   6.250   0.5939   0.05512   0.04591  -0.0156   0.5042   1.0000
   6.500   0.6011   0.05707   0.04790  -0.0141   0.4916   1.0000
   6.750   0.6128   0.05874   0.04965  -0.0127   0.4787   1.0000
   7.000   0.6248   0.06033   0.05133  -0.0111   0.4649   1.0000
   7.250   0.6387   0.06182   0.05291  -0.0095   0.4513   1.0000
   7.500   0.6498   0.06341   0.05457  -0.0078   0.4371   1.0000
   7.750   0.6621   0.06495   0.05620  -0.0061   0.4230   1.0000
   8.000   0.6196   0.07081   0.06191  -0.0062   0.4147   1.0000
   8.250   0.6229   0.07334   0.06449  -0.0053   0.4013   1.0000
   8.500   0.6274   0.07589   0.06709  -0.0046   0.3884   1.0000
   8.750   0.6341   0.07824   0.06950  -0.0038   0.3747   1.0000
   9.000   0.6435   0.08053   0.07189  -0.0030   0.3619   1.0000
   9.250   0.6536   0.08270   0.07415  -0.0021   0.3484   1.0000
   9.500   0.6638   0.08475   0.07628  -0.0012   0.3346   1.0000
   9.750   0.6379   0.09095   0.08241  -0.0034   0.3298   1.0000
  10.000   0.6474   0.09364   0.08518  -0.0030   0.3188   1.0000
  10.250   0.6576   0.09588   0.08749  -0.0023   0.3055   1.0000
  10.500   0.6390   0.10164   0.09322  -0.0045   0.3015   1.0000
  10.750   0.6295   0.10709   0.09867  -0.0065   0.3008   1.0000
  11.000   0.6219   0.11248   0.10408  -0.0084   0.3023   1.0000
  11.250   0.6170   0.11757   0.10919  -0.0102   0.3033   1.0000
  11.500   0.6264   0.12291   0.11461  -0.0115   0.3070   1.0000
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