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MH 201 13.08% (mh201-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 201 13.08% (mh201-il)
Reynolds number: 100,000
Max Cl/Cd: 54.99 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh201-il-100000.txt
Download as CSV file: xf-mh201-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 201  13.08%                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4001   0.09839   0.09380  -0.0410   1.0000   0.1236
  -8.750  -0.4562   0.09609   0.09174  -0.0436   1.0000   0.1266
  -8.500  -0.5000   0.09406   0.08985  -0.0428   1.0000   0.1269
  -8.250  -0.4413   0.09048   0.08620  -0.0370   1.0000   0.1316
  -8.000  -0.4523   0.08859   0.08439  -0.0346   1.0000   0.1342
  -7.750  -0.4758   0.08660   0.08251  -0.0325   1.0000   0.1365
  -7.500  -0.5158   0.08453   0.08057  -0.0306   1.0000   0.1384
  -7.250  -0.5836   0.08123   0.07720  -0.0339   1.0000   0.1414
  -7.000  -0.5835   0.07728   0.07333  -0.0319   1.0000   0.1440
  -6.750  -0.5735   0.07519   0.07130  -0.0285   1.0000   0.1475
  -6.500  -0.5829   0.07222   0.06830  -0.0281   1.0000   0.1524
  -5.750  -0.5727   0.04109   0.03385  -0.0372   1.0000   0.0495
  -5.500  -0.5530   0.03819   0.03072  -0.0367   1.0000   0.0480
  -5.250  -0.5322   0.03545   0.02764  -0.0364   1.0000   0.0471
  -5.000  -0.5078   0.03344   0.02516  -0.0363   0.9995   0.0480
  -4.750  -0.4699   0.03121   0.02248  -0.0385   0.9954   0.0498
  -4.500  -0.4342   0.02929   0.02042  -0.0401   0.9912   0.0512
  -4.250  -0.3990   0.02791   0.01896  -0.0415   0.9868   0.0537
  -4.000  -0.3619   0.02697   0.01786  -0.0431   0.9825   0.0589
  -3.750  -0.3305   0.02578   0.01679  -0.0443   0.9773   0.0700
  -3.500  -0.2933   0.02443   0.01565  -0.0465   0.9732   0.0991
  -3.250  -0.2616   0.02095   0.01502  -0.0488   0.9706   0.5344
  -3.000  -0.2444   0.02163   0.01609  -0.0451   0.9632   0.6754
  -2.750  -0.2238   0.02280   0.01721  -0.0420   0.9564   0.7390
  -2.500  -0.2095   0.02367   0.01802  -0.0376   0.9487   0.7751
  -2.250  -0.1939   0.02430   0.01854  -0.0339   0.9414   0.8032
  -2.000  -0.1755   0.02474   0.01884  -0.0310   0.9340   0.8297
  -1.750  -0.1638   0.02498   0.01900  -0.0268   0.9261   0.8507
  -1.500  -0.1442   0.02517   0.01906  -0.0244   0.9188   0.8740
  -1.250  -0.1318   0.02516   0.01897  -0.0208   0.9103   0.8940
  -1.000  -0.1067   0.02519   0.01887  -0.0196   0.9033   0.9147
  -0.750  -0.0847   0.02516   0.01872  -0.0184   0.8949   0.9340
  -0.500  -0.0340   0.02534   0.01873  -0.0224   0.8890   0.9508
  -0.250   0.0456   0.02571   0.01891  -0.0320   0.8861   0.9644
   0.000   0.1043   0.02593   0.01900  -0.0387   0.8782   0.9744
   0.250   0.1759   0.02597   0.01892  -0.0474   0.8734   0.9807
   0.500   0.2362   0.02596   0.01881  -0.0541   0.8672   0.9868
   0.750   0.2914   0.02586   0.01866  -0.0599   0.8596   0.9932
   1.000   0.3611   0.02549   0.01823  -0.0679   0.8559   0.9974
   1.250   0.3841   0.02549   0.01822  -0.0679   0.8440   1.0000
   1.500   0.4275   0.02512   0.01782  -0.0708   0.8376   1.0000
   1.750   0.4515   0.02492   0.01762  -0.0704   0.8268   1.0000
   2.000   0.5173   0.02410   0.01680  -0.0768   0.8235   1.0000
   2.250   0.5318   0.02398   0.01670  -0.0746   0.8108   1.0000
   2.500   0.5473   0.02384   0.01658  -0.0725   0.7982   1.0000
   2.750   0.6160   0.02276   0.01553  -0.0789   0.7942   1.0000
   3.000   0.6304   0.02259   0.01540  -0.0764   0.7811   1.0000
   3.250   0.6534   0.02222   0.01507  -0.0752   0.7691   1.0000
   3.500   0.7158   0.02105   0.01394  -0.0803   0.7627   1.0000
   3.750   0.7329   0.02076   0.01371  -0.0780   0.7488   1.0000
   4.000   0.7534   0.02039   0.01338  -0.0762   0.7349   1.0000
   4.250   0.7764   0.01998   0.01300  -0.0748   0.7208   1.0000
   4.500   0.8006   0.01954   0.01261  -0.0736   0.7061   1.0000
   4.750   0.8257   0.01910   0.01220  -0.0725   0.6902   1.0000
   5.000   0.8528   0.01866   0.01178  -0.0718   0.6728   1.0000
   5.250   0.8840   0.01821   0.01133  -0.0718   0.6541   1.0000
   5.500   0.9029   0.01810   0.01125  -0.0700   0.6309   1.0000
   5.750   0.9326   0.01785   0.01095  -0.0699   0.6068   1.0000
   6.000   0.9573   0.01784   0.01089  -0.0691   0.5788   1.0000
   6.250   0.9816   0.01798   0.01096  -0.0683   0.5483   1.0000
   6.500   1.0052   0.01828   0.01113  -0.0675   0.5163   1.0000
   6.750   1.0269   0.01872   0.01144  -0.0666   0.4834   1.0000
   7.000   1.0469   0.01928   0.01189  -0.0654   0.4502   1.0000
   7.250   1.0663   0.01993   0.01241  -0.0642   0.4180   1.0000
   7.500   1.0849   0.02068   0.01300  -0.0630   0.3873   1.0000
   7.750   1.1030   0.02149   0.01366  -0.0617   0.3583   1.0000
   8.000   1.1205   0.02237   0.01442  -0.0605   0.3312   1.0000
   8.250   1.1367   0.02328   0.01526  -0.0590   0.3054   1.0000
   8.500   1.1543   0.02429   0.01611  -0.0578   0.2826   1.0000
   8.750   1.1697   0.02528   0.01708  -0.0563   0.2609   1.0000
   9.000   1.1859   0.02633   0.01805  -0.0549   0.2417   1.0000
   9.250   1.2039   0.02749   0.01908  -0.0539   0.2242   1.0000
   9.500   1.2202   0.02865   0.02020  -0.0527   0.2080   1.0000
   9.750   1.2377   0.02987   0.02140  -0.0516   0.1934   1.0000
  10.000   1.2545   0.03111   0.02263  -0.0505   0.1799   1.0000
  10.250   1.2680   0.03232   0.02397  -0.0488   0.1680   1.0000
  10.500   1.2832   0.03371   0.02545  -0.0475   0.1569   1.0000
  10.750   1.3007   0.03520   0.02696  -0.0466   0.1467   1.0000
  11.000   1.3237   0.03681   0.02842  -0.0466   0.1363   1.0000
  11.250   1.3283   0.03820   0.03014  -0.0438   0.1289   1.0000
  11.500   1.3476   0.03998   0.03192  -0.0434   0.1205   1.0000
  11.750   1.3542   0.04152   0.03368  -0.0411   0.1138   1.0000
  12.000   1.3711   0.04360   0.03580  -0.0405   0.1068   1.0000
  12.250   1.3735   0.04537   0.03783  -0.0380   0.1014   1.0000
  12.500   1.3923   0.04765   0.04007  -0.0377   0.0950   1.0000
  12.750   1.3871   0.04984   0.04263  -0.0347   0.0912   1.0000
  13.000   1.3910   0.05174   0.04465  -0.0329   0.0867   1.0000
  13.250   1.3996   0.05465   0.04767  -0.0320   0.0824   1.0000
  13.500   1.3868   0.05756   0.05097  -0.0292   0.0801   1.0000
  13.750   1.3795   0.06043   0.05410  -0.0274   0.0772   1.0000
  14.000   1.3850   0.06266   0.05634  -0.0266   0.0736   1.0000
  14.250   1.3812   0.06674   0.06059  -0.0257   0.0712   1.0000
  14.500   1.3584   0.07101   0.06524  -0.0243   0.0705   1.0000
  14.750   1.3340   0.07593   0.07049  -0.0238   0.0698   1.0000
  15.000   1.3079   0.08155   0.07643  -0.0243   0.0694   1.0000
  15.250   1.2793   0.08797   0.08314  -0.0257   0.0694   1.0000
  15.500   1.2481   0.09537   0.09081  -0.0284   0.0697   1.0000
  15.750   1.2152   0.10387   0.09954  -0.0324   0.0703   1.0000
  16.000   1.1817   0.11351   0.10935  -0.0377   0.0710   1.0000
  16.250   1.1486   0.12426   0.12021  -0.0441   0.0718   1.0000
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