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MH 200 12.97% (mh200-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 200 12.97% (mh200-il)
Reynolds number: 500,000
Max Cl/Cd: 98.55 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh200-il-500000.txt
Download as CSV file: xf-mh200-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 200  12.97%                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3088   0.11105   0.10888  -0.0491   1.0000   0.0164
 -12.000  -0.3120   0.10664   0.10450  -0.0503   1.0000   0.0164
  -7.250  -0.3982   0.02268   0.01730  -0.0870   0.8933   0.0153
  -7.000  -0.3774   0.01897   0.01301  -0.0852   0.8869   0.0123
  -6.750  -0.3527   0.01842   0.01229  -0.0845   0.8807   0.0119
  -6.500  -0.3288   0.01718   0.01095  -0.0839   0.8749   0.0115
  -6.250  -0.3057   0.01579   0.00943  -0.0832   0.8703   0.0114
  -6.000  -0.2840   0.01478   0.00836  -0.0823   0.8649   0.0113
  -5.750  -0.2617   0.01396   0.00746  -0.0814   0.8600   0.0114
  -5.500  -0.2383   0.01331   0.00670  -0.0808   0.8558   0.0116
  -5.250  -0.2173   0.01248   0.00579  -0.0798   0.8509   0.0121
  -5.000  -0.1941   0.01182   0.00506  -0.0792   0.8466   0.0134
  -4.750  -0.1686   0.01143   0.00459  -0.0789   0.8430   0.0160
  -4.500  -0.1476   0.01038   0.00383  -0.0780   0.8391   0.0813
  -4.250  -0.1262   0.00950   0.00349  -0.0776   0.8349   0.2028
  -4.000  -0.1034   0.00873   0.00320  -0.0774   0.8312   0.3276
  -3.750  -0.0799   0.00803   0.00297  -0.0772   0.8279   0.4588
  -3.500  -0.0560   0.00751   0.00289  -0.0768   0.8244   0.5752
  -3.250  -0.0298   0.00736   0.00292  -0.0765   0.8206   0.6398
  -3.000  -0.0022   0.00737   0.00296  -0.0764   0.8173   0.6742
  -2.750   0.0262   0.00743   0.00297  -0.0764   0.8143   0.6946
  -2.500   0.0544   0.00751   0.00301  -0.0765   0.8111   0.7099
  -2.250   0.0822   0.00757   0.00305  -0.0764   0.8075   0.7222
  -2.000   0.1104   0.00763   0.00308  -0.0764   0.8040   0.7328
  -1.750   0.1391   0.00771   0.00308  -0.0766   0.8009   0.7429
  -1.500   0.1673   0.00780   0.00314  -0.0766   0.7979   0.7501
  -1.250   0.1951   0.00784   0.00317  -0.0766   0.7939   0.7582
  -1.000   0.2227   0.00789   0.00321  -0.0764   0.7898   0.7644
  -0.750   0.2515   0.00794   0.00320  -0.0766   0.7859   0.7716
  -0.500   0.2790   0.00799   0.00325  -0.0765   0.7819   0.7768
  -0.250   0.3065   0.00803   0.00329  -0.0764   0.7771   0.7834
   0.000   0.3343   0.00805   0.00330  -0.0763   0.7727   0.7895
   0.250   0.3623   0.00812   0.00335  -0.0762   0.7686   0.7950
   0.500   0.3899   0.00813   0.00336  -0.0763   0.7633   0.8006
   0.750   0.4175   0.00812   0.00335  -0.0761   0.7580   0.8043
   1.000   0.4451   0.00814   0.00337  -0.0760   0.7527   0.8083
   1.250   0.4726   0.00813   0.00336  -0.0760   0.7462   0.8127
   1.500   0.5011   0.00814   0.00333  -0.0761   0.7408   0.8166
   1.750   0.5274   0.00812   0.00337  -0.0758   0.7341   0.8201
   2.000   0.5550   0.00812   0.00337  -0.0757   0.7279   0.8242
   2.250   0.5826   0.00813   0.00340  -0.0757   0.7211   0.8287
   2.500   0.6096   0.00811   0.00339  -0.0755   0.7139   0.8322
   2.750   0.6361   0.00810   0.00344  -0.0752   0.7060   0.8355
   3.000   0.6633   0.00810   0.00343  -0.0751   0.6976   0.8391
   3.250   0.6902   0.00809   0.00346  -0.0750   0.6873   0.8428
   3.500   0.7167   0.00808   0.00348  -0.0747   0.6761   0.8459
   3.750   0.7424   0.00808   0.00351  -0.0743   0.6627   0.8488
   4.000   0.7680   0.00810   0.00355  -0.0738   0.6463   0.8522
   4.250   0.7931   0.00816   0.00358  -0.0733   0.6250   0.8558
   4.500   0.8170   0.00829   0.00364  -0.0726   0.5944   0.8592
   4.750   0.8376   0.00852   0.00375  -0.0712   0.5571   0.8625
   5.000   0.8574   0.00887   0.00395  -0.0697   0.5164   0.8662
   5.250   0.8759   0.00932   0.00420  -0.0681   0.4705   0.8703
   5.500   0.8941   0.00979   0.00450  -0.0665   0.4260   0.8743
   5.750   0.9113   0.01025   0.00481  -0.0647   0.3843   0.8782
   6.000   0.9289   0.01074   0.00515  -0.0631   0.3439   0.8827
   6.250   0.9468   0.01125   0.00550  -0.0616   0.3060   0.8876
   6.500   0.9636   0.01170   0.00584  -0.0597   0.2743   0.8921
   6.750   0.9810   0.01216   0.00621  -0.0581   0.2453   0.8974
   7.000   0.9978   0.01264   0.00659  -0.0564   0.2174   0.9031
   7.250   1.0132   0.01308   0.00696  -0.0544   0.1948   0.9096
   7.500   1.0288   0.01348   0.00732  -0.0524   0.1742   0.9169
   7.750   1.0412   0.01387   0.00768  -0.0497   0.1567   0.9260
   8.000   1.0525   0.01428   0.00806  -0.0469   0.1397   0.9385
   8.250   1.0651   0.01469   0.00848  -0.0444   0.1222   0.9599
   8.500   1.0871   0.01532   0.00904  -0.0442   0.1024   1.0000
   8.750   1.1055   0.01601   0.00965  -0.0434   0.0855   1.0000
   9.000   1.1224   0.01674   0.01031  -0.0423   0.0703   1.0000
   9.250   1.1377   0.01753   0.01104  -0.0409   0.0579   1.0000
   9.500   1.1521   0.01835   0.01184  -0.0394   0.0485   1.0000
   9.750   1.1633   0.01937   0.01281  -0.0375   0.0407   1.0000
  10.000   1.1799   0.02003   0.01356  -0.0364   0.0369   1.0000
  10.250   1.1911   0.02106   0.01457  -0.0346   0.0325   1.0000
  10.500   1.2043   0.02195   0.01553  -0.0332   0.0293   1.0000
  10.750   1.2192   0.02274   0.01635  -0.0320   0.0262   1.0000
  11.000   1.2247   0.02421   0.01784  -0.0298   0.0228   1.0000
  11.250   1.2427   0.02479   0.01849  -0.0291   0.0210   1.0000
  11.500   1.2574   0.02562   0.01932  -0.0282   0.0183   1.0000
  11.750   1.2619   0.02724   0.02101  -0.0262   0.0163   1.0000
  12.000   1.2787   0.02794   0.02177  -0.0256   0.0145   1.0000
  12.250   1.2901   0.02908   0.02294  -0.0245   0.0127   1.0000
  12.500   1.2936   0.03089   0.02484  -0.0228   0.0112   1.0000
  12.750   1.3052   0.03205   0.02609  -0.0219   0.0098   1.0000
  13.000   1.3111   0.03373   0.02782  -0.0206   0.0085   1.0000
  13.250   1.3141   0.03574   0.02992  -0.0193   0.0073   1.0000
  13.500   1.3207   0.03746   0.03173  -0.0184   0.0062   1.0000
  13.750   1.3207   0.03983   0.03419  -0.0173   0.0056   1.0000
  14.000   1.3157   0.04281   0.03731  -0.0161   0.0051   1.0000
  14.250   1.3174   0.04522   0.03985  -0.0155   0.0047   1.0000
  14.500   1.3203   0.04759   0.04231  -0.0151   0.0040   1.0000
  14.750   1.3163   0.05082   0.04569  -0.0148   0.0042   1.0000
  15.000   1.3127   0.05417   0.04915  -0.0148   0.0038   1.0000
  15.250   1.3075   0.05790   0.05300  -0.0152   0.0037   1.0000
  15.500   1.2959   0.06267   0.05795  -0.0160   0.0036   1.0000
  15.750   1.2751   0.06912   0.06458  -0.0176   0.0034   1.0000
  16.000   1.2672   0.07399   0.06960  -0.0192   0.0034   1.0000
  16.250   1.2610   0.07890   0.07467  -0.0211   0.0032   1.0000
  16.500   1.2514   0.08454   0.08047  -0.0236   0.0032   1.0000
  16.750   1.2389   0.09086   0.08694  -0.0264   0.0033   1.0000
  17.000   1.2283   0.09717   0.09342  -0.0296   0.0031   1.0000
  17.250   1.2149   0.10412   0.10051  -0.0331   0.0032   1.0000
  17.500   1.2013   0.11132   0.10786  -0.0370   0.0031   1.0000
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