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MH33 (mh33-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: MH33 (mh33-il)
Reynolds number: 1,000,000
Max Cl/Cd: 74.65 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh33-il-1000000-n5.txt
Download as CSV file: xf-mh33-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH33                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5642   0.08051   0.07891  -0.0160   1.0000   0.0015
  -8.750  -0.5684   0.07593   0.07436  -0.0188   1.0000   0.0014
  -8.500  -0.5785   0.07066   0.06912  -0.0227   1.0000   0.0014
  -8.250  -0.5917   0.06465   0.06311  -0.0279   1.0000   0.0014
  -8.000  -0.5998   0.05741   0.05579  -0.0323   1.0000   0.0014
  -7.750  -0.6088   0.04974   0.04797  -0.0340   1.0000   0.0014
  -7.500  -0.6179   0.04209   0.04007  -0.0333   1.0000   0.0013
  -7.250  -0.6369   0.02879   0.02608  -0.0301   0.9989   0.0014
  -7.000  -0.6178   0.02237   0.01901  -0.0307   0.9957   0.0017
  -6.750  -0.5908   0.01995   0.01624  -0.0314   0.9940   0.0018
  -6.500  -0.5638   0.01874   0.01484  -0.0317   0.9918   0.0019
  -6.250  -0.5390   0.01608   0.01175  -0.0317   0.9891   0.0020
  -6.000  -0.5119   0.01418   0.00956  -0.0320   0.9869   0.0023
  -5.750  -0.4821   0.01314   0.00837  -0.0327   0.9852   0.0024
  -5.500  -0.4513   0.01231   0.00743  -0.0336   0.9837   0.0025
  -5.250  -0.4201   0.01152   0.00654  -0.0345   0.9822   0.0027
  -5.000  -0.3910   0.01101   0.00597  -0.0349   0.9793   0.0029
  -4.750  -0.3628   0.01054   0.00541  -0.0350   0.9751   0.0033
  -4.500  -0.3338   0.00992   0.00471  -0.0353   0.9715   0.0035
  -4.250  -0.3038   0.00928   0.00397  -0.0357   0.9684   0.0036
  -4.000  -0.2785   0.00877   0.00337  -0.0351   0.9623   0.0036
  -3.750  -0.2506   0.00832   0.00283  -0.0350   0.9570   0.0036
  -3.500  -0.2236   0.00800   0.00242  -0.0347   0.9507   0.0036
  -3.250  -0.1965   0.00773   0.00209  -0.0343   0.9435   0.0038
  -3.000  -0.1698   0.00753   0.00180  -0.0340   0.9353   0.0040
  -2.750  -0.1428   0.00736   0.00157  -0.0336   0.9263   0.0055
  -2.500  -0.1174   0.00693   0.00132  -0.0331   0.9152   0.0522
  -2.250  -0.0916   0.00663   0.00116  -0.0327   0.9019   0.0980
  -2.000  -0.0666   0.00621   0.00101  -0.0322   0.8862   0.1846
  -1.750  -0.0416   0.00585   0.00089  -0.0317   0.8669   0.2690
  -1.500  -0.0160   0.00569   0.00079  -0.0312   0.8432   0.3179
  -1.250   0.0094   0.00557   0.00071  -0.0307   0.8143   0.3673
  -1.000   0.0346   0.00549   0.00065  -0.0301   0.7816   0.4169
  -0.750   0.0599   0.00542   0.00061  -0.0296   0.7473   0.4700
  -0.500   0.0849   0.00534   0.00057  -0.0291   0.7118   0.5321
  -0.250   0.1099   0.00527   0.00056  -0.0285   0.6750   0.5948
   0.000   0.1349   0.00523   0.00057  -0.0280   0.6374   0.6514
   0.250   0.1597   0.00520   0.00058  -0.0274   0.5990   0.7115
   0.500   0.1841   0.00516   0.00062  -0.0266   0.5614   0.7731
   0.750   0.2074   0.00512   0.00068  -0.0256   0.5248   0.8408
   1.000   0.2305   0.00517   0.00077  -0.0244   0.4887   0.8954
   1.250   0.2548   0.00532   0.00085  -0.0235   0.4526   0.9255
   1.500   0.2801   0.00551   0.00092  -0.0228   0.4151   0.9434
   1.750   0.3063   0.00570   0.00100  -0.0225   0.3785   0.9561
   2.000   0.3340   0.00591   0.00109  -0.0225   0.3438   0.9658
   2.250   0.3637   0.00610   0.00117  -0.0229   0.3123   0.9732
   2.500   0.3924   0.00632   0.00127  -0.0232   0.2804   0.9809
   2.750   0.4258   0.00656   0.00137  -0.0246   0.2461   0.9849
   3.000   0.4586   0.00682   0.00152  -0.0258   0.2108   0.9885
   3.250   0.4906   0.00707   0.00166  -0.0269   0.1818   0.9920
   3.500   0.5229   0.00735   0.00181  -0.0281   0.1503   0.9950
   3.750   0.5560   0.00761   0.00198  -0.0295   0.1261   0.9978
   4.000   0.5872   0.00795   0.00217  -0.0304   0.0953   1.0000
   4.250   0.6100   0.00822   0.00239  -0.0295   0.0753   1.0000
   4.500   0.6329   0.00850   0.00259  -0.0286   0.0593   1.0000
   4.750   0.6558   0.00881   0.00283  -0.0277   0.0419   1.0000
   5.000   0.6780   0.00924   0.00312  -0.0267   0.0211   1.0000
   5.250   0.7012   0.00956   0.00340  -0.0258   0.0128   1.0000
   5.500   0.7253   0.00982   0.00366  -0.0251   0.0101   1.0000
   5.750   0.7495   0.01010   0.00394  -0.0245   0.0080   1.0000
   6.000   0.7741   0.01037   0.00427  -0.0239   0.0063   1.0000
   6.250   0.7979   0.01077   0.00465  -0.0233   0.0027   1.0000
   6.500   0.8219   0.01118   0.00507  -0.0226   0.0012   1.0000
   6.750   0.8463   0.01155   0.00550  -0.0220   0.0010   1.0000
   7.000   0.8704   0.01198   0.00600  -0.0214   0.0009   1.0000
   7.250   0.8945   0.01243   0.00652  -0.0207   0.0008   1.0000
   7.500   0.9181   0.01296   0.00714  -0.0201   0.0008   1.0000
   7.750   0.9412   0.01356   0.00784  -0.0193   0.0007   1.0000
   8.000   0.9640   0.01423   0.00862  -0.0185   0.0007   1.0000
   8.250   0.9864   0.01494   0.00944  -0.0176   0.0007   1.0000
   8.500   1.0080   0.01575   0.01042  -0.0167   0.0007   1.0000
   8.750   1.0282   0.01678   0.01163  -0.0156   0.0007   1.0000
   9.000   1.0478   0.01787   0.01289  -0.0144   0.0007   1.0000
   9.250   1.0658   0.01917   0.01438  -0.0130   0.0007   1.0000
   9.500   1.0835   0.02046   0.01586  -0.0117   0.0007   1.0000
   9.750   1.0974   0.02230   0.01797  -0.0098   0.0007   1.0000
  10.000   1.1111   0.02404   0.01995  -0.0081   0.0007   1.0000
  10.250   1.1188   0.02650   0.02274  -0.0057   0.0007   1.0000
  10.500   1.1240   0.02902   0.02556  -0.0033   0.0007   1.0000
  10.750   1.1214   0.03216   0.02904  -0.0002   0.0007   1.0000
  11.000   1.1126   0.03518   0.03236   0.0034   0.0007   1.0000
  11.250   1.0928   0.03832   0.03574   0.0079   0.0007   1.0000
  11.500   1.0850   0.04064   0.03821   0.0101   0.0007   1.0000
  11.750   1.0584   0.04537   0.04317   0.0109   0.0007   1.0000
  12.000   1.0439   0.04984   0.04779   0.0093   0.0007   1.0000
  12.250   1.0157   0.05866   0.05681   0.0027   0.0007   1.0000
  12.500   1.0099   0.06532   0.06356  -0.0028   0.0007   1.0000
  12.750   0.9838   0.07820   0.07657  -0.0116   0.0007   1.0000
  13.000   0.9466   0.09252   0.09097  -0.0192   0.0007   1.0000
  13.250   0.9325   0.10052   0.09898  -0.0232   0.0007   1.0000
  13.500   0.9037   0.11230   0.11078  -0.0291   0.0007   1.0000
  13.750   0.8703   0.12599   0.12448  -0.0357   0.0008   1.0000
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