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MH 200 12.97% (mh200-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: MH 200 12.97% (mh200-il)
Reynolds number: 1,000,000
Max Cl/Cd: 116.97 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh200-il-1000000.txt
Download as CSV file: xf-mh200-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4816   0.01881   0.01393  -0.0840   0.8572   0.0064
  -7.750  -0.4617   0.01731   0.01220  -0.0829   0.8505   0.0063
  -7.500  -0.4404   0.01613   0.01086  -0.0820   0.8442   0.0063
  -7.250  -0.4187   0.01507   0.00965  -0.0811   0.8386   0.0062
  -7.000  -0.3969   0.01410   0.00857  -0.0802   0.8330   0.0062
  -6.750  -0.3736   0.01354   0.00794  -0.0797   0.8283   0.0064
  -6.500  -0.3497   0.01303   0.00736  -0.0793   0.8239   0.0067
  -6.250  -0.3263   0.01240   0.00667  -0.0787   0.8195   0.0068
  -6.000  -0.3026   0.01185   0.00604  -0.0782   0.8154   0.0070
  -5.750  -0.2789   0.01126   0.00536  -0.0776   0.8115   0.0070
  -5.500  -0.2545   0.01073   0.00477  -0.0772   0.8078   0.0071
  -5.250  -0.2292   0.01030   0.00427  -0.0768   0.8042   0.0072
  -5.000  -0.2034   0.00994   0.00383  -0.0766   0.8008   0.0075
  -4.750  -0.1770   0.00965   0.00347  -0.0765   0.7975   0.0079
  -4.500  -0.1509   0.00924   0.00302  -0.0762   0.7944   0.0104
  -4.250  -0.1262   0.00861   0.00259  -0.0759   0.7910   0.0539
  -4.000  -0.1014   0.00804   0.00231  -0.0758   0.7877   0.1281
  -3.750  -0.0755   0.00763   0.00211  -0.0759   0.7845   0.1953
  -3.500  -0.0500   0.00709   0.00193  -0.0760   0.7815   0.2899
  -3.250  -0.0254   0.00636   0.00173  -0.0760   0.7782   0.4318
  -3.000   0.0010   0.00590   0.00159  -0.0761   0.7751   0.5304
  -2.750   0.0282   0.00563   0.00153  -0.0762   0.7722   0.6048
  -2.500   0.0566   0.00557   0.00152  -0.0764   0.7691   0.6418
  -2.250   0.0851   0.00552   0.00151  -0.0766   0.7663   0.6663
  -2.000   0.1138   0.00551   0.00150  -0.0768   0.7630   0.6830
  -1.750   0.1425   0.00551   0.00150  -0.0770   0.7596   0.6965
  -1.500   0.1713   0.00555   0.00150  -0.0772   0.7559   0.7072
  -1.250   0.2000   0.00557   0.00150  -0.0774   0.7522   0.7160
  -1.000   0.2287   0.00558   0.00151  -0.0776   0.7482   0.7236
  -0.750   0.2575   0.00560   0.00151  -0.0778   0.7444   0.7304
  -0.250   0.3150   0.00567   0.00154  -0.0783   0.7364   0.7426
   0.000   0.3433   0.00566   0.00155  -0.0784   0.7318   0.7475
   0.250   0.3718   0.00571   0.00156  -0.0785   0.7268   0.7529
   0.500   0.4003   0.00573   0.00158  -0.0787   0.7216   0.7585
   0.750   0.4284   0.00573   0.00161  -0.0788   0.7162   0.7636
   1.000   0.4568   0.00579   0.00164  -0.0789   0.7111   0.7682
   1.500   0.5134   0.00580   0.00167  -0.0792   0.6994   0.7755
   1.750   0.5416   0.00582   0.00171  -0.0793   0.6932   0.7788
   2.000   0.5697   0.00585   0.00174  -0.0794   0.6858   0.7822
   2.250   0.5980   0.00589   0.00177  -0.0796   0.6778   0.7856
   2.500   0.6255   0.00592   0.00180  -0.0796   0.6686   0.7889
   2.750   0.6530   0.00595   0.00185  -0.0795   0.6569   0.7923
   3.000   0.6801   0.00601   0.00191  -0.0794   0.6422   0.7960
   3.250   0.7068   0.00611   0.00196  -0.0793   0.6230   0.7994
   3.500   0.7322   0.00626   0.00203  -0.0789   0.5960   0.8023
   3.750   0.7559   0.00649   0.00215  -0.0782   0.5604   0.8051
   4.000   0.7789   0.00680   0.00232  -0.0773   0.5227   0.8079
   4.250   0.8015   0.00715   0.00252  -0.0765   0.4826   0.8110
   4.500   0.8238   0.00754   0.00274  -0.0756   0.4409   0.8139
   4.750   0.8453   0.00795   0.00298  -0.0747   0.3972   0.8167
   5.000   0.8672   0.00832   0.00321  -0.0737   0.3593   0.8196
   5.250   0.8888   0.00873   0.00347  -0.0728   0.3233   0.8226
   5.500   0.9102   0.00915   0.00375  -0.0718   0.2864   0.8258
   5.750   0.9320   0.00955   0.00402  -0.0710   0.2565   0.8289
   6.000   0.9536   0.00992   0.00429  -0.0700   0.2293   0.8320
   6.250   0.9744   0.01032   0.00458  -0.0690   0.2022   0.8352
   6.500   0.9958   0.01069   0.00488  -0.0680   0.1811   0.8387
   6.750   1.0176   0.01104   0.00518  -0.0672   0.1628   0.8424
   7.000   1.0384   0.01142   0.00549  -0.0661   0.1442   0.8459
   7.250   1.0582   0.01182   0.00583  -0.0649   0.1260   0.8496
   7.500   1.0782   0.01221   0.00617  -0.0637   0.1101   0.8538
   7.750   1.0977   0.01264   0.00654  -0.0625   0.0950   0.8583
   8.000   1.1149   0.01308   0.00695  -0.0608   0.0797   0.8630
   8.250   1.1293   0.01357   0.00737  -0.0586   0.0646   0.8685
   8.500   1.1442   0.01406   0.00782  -0.0565   0.0528   0.8746
   8.750   1.1585   0.01455   0.00829  -0.0544   0.0430   0.8816
   9.000   1.1738   0.01502   0.00876  -0.0525   0.0357   0.8893
   9.250   1.1881   0.01550   0.00926  -0.0504   0.0301   0.8988
   9.500   1.2024   0.01595   0.00975  -0.0483   0.0265   0.9108
  10.000   1.2305   0.01678   0.01076  -0.0442   0.0205   1.0000
  10.250   1.2466   0.01741   0.01139  -0.0429   0.0180   1.0000
  10.500   1.2624   0.01805   0.01205  -0.0416   0.0160   1.0000
  10.750   1.2789   0.01863   0.01266  -0.0403   0.0146   1.0000
  11.000   1.2936   0.01934   0.01337  -0.0389   0.0130   1.0000
  11.250   1.3071   0.02012   0.01419  -0.0374   0.0114   1.0000
  11.500   1.3226   0.02078   0.01489  -0.0362   0.0102   1.0000
  11.750   1.3355   0.02162   0.01576  -0.0348   0.0089   1.0000
  12.000   1.3482   0.02250   0.01667  -0.0334   0.0073   1.0000
  12.250   1.3584   0.02358   0.01775  -0.0318   0.0050   1.0000
  12.500   1.3691   0.02465   0.01887  -0.0303   0.0043   1.0000
  12.750   1.3762   0.02602   0.02029  -0.0285   0.0030   1.0000
  13.000   1.3848   0.02730   0.02164  -0.0270   0.0026   1.0000
  13.250   1.3874   0.02911   0.02355  -0.0251   0.0019   1.0000
  13.500   1.3949   0.03055   0.02508  -0.0238   0.0017   1.0000
  13.750   1.4020   0.03206   0.02668  -0.0225   0.0016   1.0000
  14.000   1.4075   0.03374   0.02846  -0.0213   0.0015   1.0000
  14.250   1.4118   0.03558   0.03040  -0.0201   0.0014   1.0000
  14.500   1.4107   0.03799   0.03292  -0.0188   0.0012   1.0000
  14.750   1.4183   0.03961   0.03462  -0.0181   0.0013   1.0000
  15.000   1.4103   0.04288   0.03805  -0.0170   0.0012   1.0000
  15.250   1.4117   0.04530   0.04057  -0.0164   0.0012   1.0000
  15.500   1.4063   0.04859   0.04399  -0.0160   0.0011   1.0000
  15.750   1.3908   0.05328   0.04887  -0.0159   0.0011   1.0000
  16.000   1.3911   0.05627   0.05196  -0.0161   0.0011   1.0000
  16.250   1.3678   0.06262   0.05854  -0.0172   0.0010   1.0000
  16.500   1.3575   0.06760   0.06365  -0.0186   0.0010   1.0000
  16.750   1.3512   0.07219   0.06836  -0.0202   0.0010   1.0000
  17.000   1.3336   0.07892   0.07526  -0.0229   0.0010   1.0000
  17.250   1.3202   0.08528   0.08178  -0.0257   0.0010   1.0000
  17.500   1.3016   0.09288   0.08954  -0.0294   0.0010   1.0000
  17.750   1.2852   0.10043   0.09723  -0.0333   0.0010   1.0000
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