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MH 22 7.2% (mh22-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: MH 22 7.2% (mh22-il)
Reynolds number: 1,000,000
Max Cl/Cd: 92.73 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh22-il-1000000.txt
Download as CSV file: xf-mh22-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 22  7.2%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4520   0.08126   0.07986   0.0025   1.0000   0.0048
  -8.000  -0.4528   0.07659   0.07520   0.0007   1.0000   0.0049
  -7.750  -0.4548   0.07198   0.07061  -0.0012   1.0000   0.0049
  -7.500  -0.4576   0.06752   0.06617  -0.0031   1.0000   0.0050
  -7.250  -0.4642   0.06313   0.06180  -0.0051   1.0000   0.0050
  -7.000  -0.4735   0.05837   0.05706  -0.0086   1.0000   0.0049
  -6.750  -0.4737   0.05257   0.05124  -0.0133   1.0000   0.0049
  -6.500  -0.4705   0.04622   0.04484  -0.0177   1.0000   0.0049
  -6.250  -0.4623   0.04015   0.03867  -0.0212   1.0000   0.0050
  -6.000  -0.4514   0.03416   0.03255  -0.0236   1.0000   0.0051
  -5.750  -0.4375   0.02865   0.02688  -0.0251   1.0000   0.0054
  -5.500  -0.4187   0.02398   0.02204  -0.0260   0.9933   0.0057
  -5.250  -0.3883   0.02156   0.01942  -0.0270   0.9316   0.0064
  -5.000  -0.3762   0.01814   0.01561  -0.0253   0.8816   0.0064
  -4.250  -0.3268   0.01281   0.00801  -0.0229   0.8512   0.0032
  -3.750  -0.2781   0.01022   0.00477  -0.0206   0.7991   0.0031
  -3.500  -0.2527   0.00949   0.00385  -0.0199   0.7796   0.0037
  -3.250  -0.2264   0.00909   0.00333  -0.0194   0.7627   0.0045
  -3.000  -0.1998   0.00873   0.00285  -0.0190   0.7484   0.0053
  -2.750  -0.1730   0.00839   0.00238  -0.0186   0.7359   0.0058
  -2.500  -0.1459   0.00816   0.00207  -0.0183   0.7248   0.0071
  -2.250  -0.1186   0.00785   0.00155  -0.0179   0.7150   0.0089
  -2.000  -0.0930   0.00718   0.00125  -0.0175   0.7057   0.1086
  -1.750  -0.0666   0.00684   0.00113  -0.0173   0.6971   0.1834
  -1.500  -0.0403   0.00651   0.00101  -0.0171   0.6890   0.2653
  -1.250  -0.0144   0.00610   0.00093  -0.0169   0.6808   0.3758
  -1.000   0.0106   0.00563   0.00086  -0.0165   0.6734   0.5174
  -0.750   0.0346   0.00515   0.00082  -0.0158   0.6658   0.6642
  -0.500   0.0573   0.00470   0.00079  -0.0146   0.6587   0.7974
  -0.250   0.0930   0.00437   0.00082  -0.0158   0.6512   0.9519
   0.000   0.1388   0.00443   0.00083  -0.0197   0.6429   0.9828
   0.250   0.1801   0.00450   0.00083  -0.0226   0.6348   0.9930
   0.500   0.2240   0.00453   0.00080  -0.0262   0.6257   0.9985
   0.750   0.2561   0.00455   0.00078  -0.0272   0.6166   1.0000
   1.000   0.2820   0.00458   0.00078  -0.0267   0.6075   1.0000
   1.250   0.3079   0.00463   0.00077  -0.0263   0.5974   1.0000
   1.500   0.3340   0.00467   0.00078  -0.0259   0.5859   1.0000
   1.750   0.3601   0.00472   0.00079  -0.0254   0.5726   1.0000
   2.000   0.3861   0.00478   0.00081  -0.0250   0.5575   1.0000
   2.250   0.4122   0.00486   0.00086  -0.0246   0.5386   1.0000
   2.500   0.4381   0.00497   0.00089  -0.0242   0.5159   1.0000
   2.750   0.4639   0.00510   0.00095  -0.0238   0.4903   1.0000
   3.000   0.4896   0.00528   0.00102  -0.0234   0.4609   1.0000
   3.500   0.5386   0.00607   0.00133  -0.0224   0.3355   1.0000
   3.750   0.5629   0.00650   0.00151  -0.0220   0.2739   1.0000
   4.000   0.5861   0.00717   0.00177  -0.0214   0.1865   1.0000
   4.250   0.6069   0.00831   0.00229  -0.0207   0.0576   1.0000
   4.500   0.6299   0.00906   0.00278  -0.0199   0.0032   1.0000
   4.750   0.6555   0.00933   0.00314  -0.0194   0.0023   1.0000
   5.000   0.6805   0.00972   0.00365  -0.0187   0.0022   1.0000
   5.250   0.7049   0.01024   0.00430  -0.0179   0.0022   1.0000
   5.500   0.7289   0.01083   0.00499  -0.0171   0.0023   1.0000
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