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MH 38 9.68% (mh38-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: MH 38 9.68% (mh38-il)
Reynolds number: 500,000
Max Cl/Cd: 114.53 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh38-il-500000-n5.txt
Download as CSV file: xf-mh38-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 38  9.68%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3354   0.08149   0.07931  -0.0476   0.9595   0.0031
  -8.750  -0.3308   0.06996   0.06777  -0.0608   0.9283   0.0029
  -8.500  -0.4459   0.03367   0.03079  -0.0888   0.8594   0.0024
  -8.000  -0.4266   0.02407   0.02009  -0.0924   0.8345   0.0024
  -7.750  -0.4083   0.02129   0.01684  -0.0927   0.8249   0.0024
  -7.500  -0.3872   0.01923   0.01438  -0.0928   0.8165   0.0024
  -7.250  -0.3643   0.01751   0.01232  -0.0927   0.8081   0.0025
  -7.000  -0.3400   0.01625   0.01080  -0.0926   0.8006   0.0026
  -6.750  -0.3148   0.01523   0.00955  -0.0925   0.7932   0.0027
  -6.500  -0.2889   0.01439   0.00851  -0.0925   0.7864   0.0028
  -6.250  -0.2627   0.01367   0.00761  -0.0924   0.7795   0.0030
  -6.000  -0.2360   0.01301   0.00676  -0.0923   0.7732   0.0034
  -5.750  -0.2091   0.01244   0.00602  -0.0922   0.7667   0.0037
  -5.500  -0.1819   0.01196   0.00540  -0.0922   0.7608   0.0042
  -5.250  -0.1548   0.01139   0.00471  -0.0921   0.7546   0.0055
  -5.000  -0.1274   0.01102   0.00423  -0.0921   0.7490   0.0072
  -4.750  -0.0998   0.01062   0.00382  -0.0921   0.7431   0.0122
  -4.500  -0.0724   0.01030   0.00350  -0.0921   0.7376   0.0214
  -4.250  -0.0448   0.01002   0.00319  -0.0922   0.7322   0.0315
  -4.000  -0.0170   0.00977   0.00293  -0.0922   0.7266   0.0420
  -3.750   0.0108   0.00957   0.00270  -0.0922   0.7216   0.0533
  -3.500   0.0388   0.00937   0.00251  -0.0923   0.7161   0.0660
  -3.250   0.0667   0.00920   0.00233  -0.0923   0.7109   0.0802
  -3.000   0.0947   0.00906   0.00217  -0.0924   0.7058   0.0932
  -2.750   0.1228   0.00892   0.00201  -0.0925   0.7005   0.1063
  -2.250   0.1789   0.00866   0.00178  -0.0926   0.6903   0.1429
  -2.000   0.2069   0.00854   0.00169  -0.0927   0.6850   0.1658
  -1.750   0.2349   0.00843   0.00160  -0.0927   0.6801   0.1885
  -1.500   0.2630   0.00830   0.00153  -0.0928   0.6746   0.2184
  -1.250   0.2909   0.00819   0.00147  -0.0929   0.6695   0.2508
  -1.000   0.3189   0.00807   0.00143  -0.0930   0.6644   0.2873
  -0.750   0.3468   0.00794   0.00140  -0.0931   0.6589   0.3329
  -0.500   0.3746   0.00782   0.00139  -0.0932   0.6539   0.3830
  -0.250   0.4025   0.00768   0.00139  -0.0933   0.6482   0.4360
   0.000   0.4302   0.00756   0.00140  -0.0933   0.6427   0.4937
   0.250   0.4577   0.00741   0.00143  -0.0933   0.6373   0.5588
   0.500   0.4849   0.00726   0.00147  -0.0933   0.6314   0.6297
   0.750   0.5113   0.00709   0.00152  -0.0929   0.6259   0.7105
   1.000   0.5352   0.00683   0.00159  -0.0920   0.6198   0.8161
   1.250   0.5634   0.00659   0.00159  -0.0916   0.6139   0.9662
   1.500   0.5948   0.00663   0.00161  -0.0924   0.6071   1.0000
   1.750   0.6224   0.00672   0.00164  -0.0923   0.6005   1.0000
   2.000   0.6503   0.00679   0.00169  -0.0924   0.5930   1.0000
   2.250   0.6778   0.00689   0.00177  -0.0923   0.5856   1.0000
   2.500   0.7055   0.00697   0.00183  -0.0923   0.5771   1.0000
   2.750   0.7331   0.00707   0.00191  -0.0923   0.5685   1.0000
   3.250   0.7878   0.00729   0.00211  -0.0922   0.5492   1.0000
   3.500   0.8151   0.00740   0.00221  -0.0921   0.5388   1.0000
   3.750   0.8421   0.00754   0.00233  -0.0920   0.5276   1.0000
   4.000   0.8690   0.00769   0.00246  -0.0919   0.5148   1.0000
   4.250   0.8957   0.00785   0.00263  -0.0917   0.5002   1.0000
   4.500   0.9220   0.00805   0.00280  -0.0915   0.4834   1.0000
   4.750   0.9478   0.00828   0.00299  -0.0912   0.4638   1.0000
   5.000   0.9730   0.00857   0.00320  -0.0909   0.4388   1.0000
   5.250   0.9972   0.00895   0.00347  -0.0904   0.4073   1.0000
   5.500   1.0192   0.00953   0.00383  -0.0896   0.3578   1.0000
   5.750   1.0404   0.01020   0.00429  -0.0888   0.3065   1.0000
   6.000   1.0622   0.01081   0.00472  -0.0880   0.2653   1.0000
   6.250   1.0817   0.01163   0.00527  -0.0870   0.2113   1.0000
   6.500   1.0990   0.01263   0.00594  -0.0857   0.1497   1.0000
   6.750   1.1149   0.01373   0.00669  -0.0842   0.0904   1.0000
   7.000   1.1309   0.01477   0.00747  -0.0827   0.0464   1.0000
   7.250   1.1479   0.01567   0.00821  -0.0812   0.0215   1.0000
   7.500   1.1668   0.01636   0.00886  -0.0800   0.0116   1.0000
   7.750   1.1853   0.01706   0.00956  -0.0788   0.0067   1.0000
   8.000   1.2039   0.01772   0.01032  -0.0774   0.0048   1.0000
   8.250   1.2198   0.01855   0.01121  -0.0758   0.0037   1.0000
   8.500   1.2336   0.01947   0.01225  -0.0737   0.0033   1.0000
   8.750   1.2465   0.02024   0.01312  -0.0716   0.0031   1.0000
   9.000   1.2563   0.02113   0.01410  -0.0690   0.0030   1.0000
   9.250   1.2653   0.02209   0.01516  -0.0664   0.0029   1.0000
   9.500   1.2745   0.02308   0.01624  -0.0642   0.0027   1.0000
   9.750   1.2836   0.02413   0.01737  -0.0621   0.0025   1.0000
  10.000   1.2933   0.02519   0.01851  -0.0602   0.0023   1.0000
  10.250   1.3026   0.02634   0.01973  -0.0585   0.0021   1.0000
  10.500   1.3126   0.02748   0.02094  -0.0570   0.0020   1.0000
  10.750   1.3173   0.02913   0.02273  -0.0552   0.0019   1.0000
  11.000   1.3211   0.03093   0.02464  -0.0535   0.0018   1.0000
  11.250   1.3219   0.03313   0.02697  -0.0517   0.0017   1.0000
  11.500   1.3208   0.03562   0.02960  -0.0501   0.0016   1.0000
  11.750   1.3255   0.03762   0.03172  -0.0489   0.0016   1.0000
  12.000   1.3295   0.03975   0.03398  -0.0479   0.0016   1.0000
  12.250   1.3319   0.04213   0.03650  -0.0470   0.0015   1.0000
  12.500   1.3340   0.04463   0.03913  -0.0462   0.0015   1.0000
  12.750   1.3351   0.04731   0.04197  -0.0455   0.0015   1.0000
  13.000   1.3367   0.05002   0.04482  -0.0451   0.0014   1.0000
  13.250   1.3356   0.05312   0.04809  -0.0448   0.0014   1.0000
  13.500   1.3341   0.05638   0.05150  -0.0447   0.0014   1.0000
  13.750   1.3317   0.05990   0.05518  -0.0448   0.0013   1.0000
  14.000   1.3276   0.06377   0.05923  -0.0452   0.0013   1.0000
  14.250   1.3216   0.06812   0.06376  -0.0459   0.0013   1.0000
  14.500   1.3145   0.07282   0.06864  -0.0470   0.0012   1.0000
  14.750   1.3075   0.07769   0.07369  -0.0484   0.0012   1.0000
  15.000   1.2972   0.08337   0.07956  -0.0504   0.0012   1.0000
  15.250   1.2861   0.08945   0.08583  -0.0528   0.0012   1.0000
  15.500   1.2753   0.09574   0.09230  -0.0555   0.0011   1.0000
  15.750   1.2622   0.10281   0.09955  -0.0589   0.0011   1.0000
  16.000   1.2488   0.11025   0.10717  -0.0628   0.0011   1.0000
  16.250   1.2334   0.11845   0.11554  -0.0672   0.0011   1.0000
  16.500   1.2174   0.12719   0.12446  -0.0722   0.0011   1.0000
  16.750   1.2020   0.13621   0.13364  -0.0775   0.0011   1.0000
  17.000   1.1857   0.14585   0.14343  -0.0833   0.0012   1.0000
  17.250   1.1686   0.15626   0.15399  -0.0897   0.0012   1.0000
  17.500   1.1513   0.16737   0.16523  -0.0964   0.0012   1.0000
  17.750   1.1315   0.18010   0.17809  -0.1038   0.0013   1.0000
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