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MH 22 7.2% (mh22-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 22 7.2% (mh22-il)
Reynolds number: 50,000
Max Cl/Cd: 33.84 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh22-il-50000.txt
Download as CSV file: xf-mh22-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.5096   0.09174   0.08576   0.0076   1.0000   0.2286
  -7.000  -0.5146   0.08885   0.08299   0.0060   1.0000   0.2390
  -6.750  -0.5101   0.08522   0.07928   0.0055   1.0000   0.2525
  -6.500  -0.5007   0.08148   0.07559   0.0061   1.0000   0.2688
  -6.250  -0.5081   0.07916   0.07336   0.0028   1.0000   0.2899
  -6.000  -0.4988   0.07569   0.06996   0.0047   1.0000   0.3163
  -5.750  -0.4799   0.07165   0.06599   0.0101   1.0000   0.3504
  -5.250  -0.4393   0.05240   0.04566  -0.0257   1.0000   0.1261
  -5.000  -0.4170   0.04613   0.03875  -0.0281   1.0000   0.1016
  -4.750  -0.3971   0.04196   0.03423  -0.0283   1.0000   0.0991
  -4.500  -0.3758   0.03815   0.02997  -0.0282   1.0000   0.0988
  -4.250  -0.3532   0.03462   0.02592  -0.0276   1.0000   0.0990
  -4.000  -0.3291   0.03125   0.02200  -0.0267   1.0000   0.0983
  -3.750  -0.3037   0.02825   0.01845  -0.0255   1.0000   0.1009
  -3.500  -0.2784   0.02559   0.01550  -0.0242   1.0000   0.1107
  -3.250  -0.2560   0.02363   0.01353  -0.0229   1.0000   0.1479
  -3.000  -0.2314   0.02122   0.01130  -0.0214   1.0000   0.2128
  -2.750  -0.1269   0.01490   0.00801  -0.0300   1.0000   1.0000
  -2.500  -0.1074   0.01476   0.00721  -0.0291   1.0000   1.0000
  -2.250  -0.0895   0.01471   0.00672  -0.0279   1.0000   1.0000
  -2.000  -0.0738   0.01473   0.00638  -0.0262   1.0000   1.0000
  -1.750  -0.0606   0.01482   0.00607  -0.0242   1.0000   1.0000
  -1.500  -0.0494   0.01498   0.00598  -0.0220   1.0000   1.0000
  -1.250  -0.0387   0.01522   0.00597  -0.0199   1.0000   1.0000
  -1.000  -0.0273   0.01549   0.00600  -0.0179   1.0000   1.0000
  -0.750  -0.0146   0.01579   0.00608  -0.0163   1.0000   1.0000
  -0.500  -0.0008   0.01612   0.00621  -0.0149   1.0000   1.0000
  -0.250   0.0138   0.01648   0.00639  -0.0137   1.0000   1.0000
   0.000   0.0291   0.01686   0.00661  -0.0127   1.0000   1.0000
   0.250   0.0448   0.01728   0.00679  -0.0119   1.0000   1.0000
   0.500   0.0607   0.01774   0.00712  -0.0112   1.0000   1.0000
   0.750   0.0768   0.01824   0.00752  -0.0106   1.0000   1.0000
   1.000   0.1009   0.01887   0.00806  -0.0117   0.9965   1.0000
   1.250   0.1588   0.01985   0.00900  -0.0191   0.9782   1.0000
   1.500   0.2143   0.02069   0.00988  -0.0257   0.9588   1.0000
   1.750   0.2712   0.02146   0.01069  -0.0323   0.9393   1.0000
   2.000   0.3254   0.02209   0.01143  -0.0380   0.9184   1.0000
   2.250   0.3818   0.02261   0.01211  -0.0438   0.8972   1.0000
   2.500   0.4390   0.02297   0.01276  -0.0490   0.8760   1.0000
   2.750   0.4783   0.02341   0.01337  -0.0508   0.8526   1.0000
   3.000   0.5151   0.02383   0.01397  -0.0517   0.8292   1.0000
   3.250   0.5486   0.02421   0.01453  -0.0516   0.8057   1.0000
   3.500   0.5796   0.02450   0.01500  -0.0506   0.7825   1.0000
   3.750   0.6037   0.02494   0.01578  -0.0486   0.7574   1.0000
   4.000   0.6263   0.02536   0.01638  -0.0463   0.7318   1.0000
   4.250   0.6484   0.02573   0.01693  -0.0437   0.7057   1.0000
   4.500   0.6703   0.02600   0.01739  -0.0408   0.6789   1.0000
   4.750   0.6923   0.02612   0.01770  -0.0376   0.6511   1.0000
   5.000   0.7125   0.02635   0.01815  -0.0346   0.6195   1.0000
   5.250   0.7344   0.02614   0.01813  -0.0309   0.5867   1.0000
   5.500   0.7557   0.02572   0.01789  -0.0270   0.5480   1.0000
   5.750   0.7759   0.02470   0.01719  -0.0222   0.4972   1.0000
   6.000   0.7905   0.02336   0.01563  -0.0165   0.4156   1.0000
   6.250   0.7896   0.02469   0.01574  -0.0110   0.2366   1.0000
   6.500   0.7952   0.02880   0.01857  -0.0078   0.1256   1.0000
   6.750   0.8166   0.03213   0.02168  -0.0056   0.0935   1.0000
   7.000   0.8420   0.03548   0.02514  -0.0040   0.0799   1.0000
   7.250   0.8617   0.03843   0.02830  -0.0028   0.0679   1.0000
   7.500   0.8829   0.04183   0.03197  -0.0016   0.0628   1.0000
   7.750   0.9016   0.04588   0.03645  -0.0004   0.0620   1.0000
   8.000   0.9139   0.05024   0.04147   0.0010   0.0628   1.0000
   8.250   0.9191   0.05504   0.04696   0.0022   0.0647   1.0000
   8.500   0.9199   0.06001   0.05243   0.0030   0.0668   1.0000
   8.750   0.9166   0.06498   0.05776   0.0034   0.0687   1.0000
   9.000   0.9124   0.06993   0.06292   0.0036   0.0704   1.0000
   9.250   0.9242   0.07566   0.06866   0.0038   0.0728   1.0000
   9.500   0.8898   0.07932   0.07271   0.0027   0.0741   1.0000
   9.750   0.8589   0.08452   0.07802  -0.0006   0.0752   1.0000
  10.000   0.8281   0.09235   0.08588  -0.0080   0.0774   1.0000
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