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MH 82 13.31% (mh82-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 82 13.31% (mh82-il)
Reynolds number: 200,000
Max Cl/Cd: 53.68 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh82-il-200000.txt
Download as CSV file: xf-mh82-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 82  13.31%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3497   0.09547   0.09242  -0.0015   0.8190   0.0482
  -8.250  -0.3712   0.09023   0.08714  -0.0097   0.7987   0.0490
  -8.000  -0.3739   0.08560   0.08246  -0.0116   0.7797   0.0494
  -7.750  -0.3542   0.08395   0.08072  -0.0074   0.7590   0.0503
  -7.500  -0.3464   0.08140   0.07809  -0.0072   0.7418   0.0513
  -7.250  -0.3448   0.07833   0.07498  -0.0086   0.7268   0.0522
  -7.000  -0.3476   0.07474   0.07131  -0.0114   0.7142   0.0534
  -6.750  -0.3663   0.06601   0.06221  -0.0250   0.7076   0.0573
  -6.500  -0.3582   0.06128   0.05741  -0.0255   0.6962   0.0582
  -6.250  -0.3419   0.05916   0.05530  -0.0245   0.6818   0.0591
  -6.000  -0.3270   0.05681   0.05290  -0.0244   0.6687   0.0607
  -5.750  -0.3142   0.05289   0.04863  -0.0267   0.6590   0.0657
  -5.500  -0.3030   0.04824   0.04371  -0.0280   0.6486   0.0688
  -5.250  -0.2837   0.04612   0.04154  -0.0278   0.6365   0.0706
  -5.000  -0.2676   0.04273   0.03754  -0.0286   0.6276   0.0792
  -4.750  -0.2493   0.02939   0.02247  -0.0264   0.6241   0.0356
  -4.500  -0.2255   0.02655   0.01952  -0.0261   0.6127   0.0338
  -4.250  -0.1991   0.02373   0.01581  -0.0247   0.6024   0.0303
  -4.000  -0.1727   0.02204   0.01382  -0.0240   0.5923   0.0300
  -3.750  -0.1452   0.02066   0.01222  -0.0234   0.5806   0.0300
  -3.500  -0.1176   0.01963   0.01092  -0.0228   0.5704   0.0304
  -3.250  -0.0909   0.01835   0.00962  -0.0223   0.5598   0.0315
  -3.000  -0.0637   0.01768   0.00891  -0.0219   0.5493   0.0339
  -2.750  -0.0370   0.01698   0.00810  -0.0213   0.5402   0.0372
  -2.500  -0.0096   0.01636   0.00747  -0.0208   0.5295   0.0410
  -2.250   0.0168   0.01569   0.00675  -0.0203   0.5208   0.0463
  -2.000   0.0437   0.01503   0.00615  -0.0198   0.5107   0.0615
  -1.750   0.0685   0.01391   0.00560  -0.0192   0.5026   0.1849
  -1.500   0.0940   0.01328   0.00543  -0.0189   0.4934   0.3023
  -1.250   0.1151   0.01235   0.00534  -0.0178   0.4858   0.5248
  -1.000   0.1307   0.01143   0.00554  -0.0138   0.4775   0.8293
  -0.750   0.1793   0.01156   0.00559  -0.0160   0.4677   0.9528
  -0.500   0.2496   0.01169   0.00539  -0.0237   0.4562   0.9878
  -0.250   0.3001   0.01175   0.00525  -0.0281   0.4464   1.0000
   0.000   0.3241   0.01185   0.00516  -0.0274   0.4396   1.0000
   0.250   0.3485   0.01197   0.00516  -0.0267   0.4322   1.0000
   0.500   0.3728   0.01208   0.00513  -0.0260   0.4252   1.0000
   0.750   0.3973   0.01227   0.00516  -0.0254   0.4192   1.0000
   1.000   0.4221   0.01241   0.00523  -0.0247   0.4124   1.0000
   1.250   0.4468   0.01259   0.00525  -0.0241   0.4068   1.0000
   1.500   0.4717   0.01280   0.00537  -0.0235   0.4009   1.0000
   1.750   0.4968   0.01296   0.00546  -0.0229   0.3947   1.0000
   2.000   0.5219   0.01318   0.00553  -0.0223   0.3896   1.0000
   2.250   0.5472   0.01343   0.00573  -0.0218   0.3842   1.0000
   2.500   0.5726   0.01364   0.00589  -0.0213   0.3789   1.0000
   2.750   0.5980   0.01387   0.00600  -0.0208   0.3744   1.0000
   3.000   0.6235   0.01418   0.00624  -0.0203   0.3697   1.0000
   3.250   0.6493   0.01440   0.00646  -0.0199   0.3644   1.0000
   3.500   0.6752   0.01464   0.00662  -0.0195   0.3599   1.0000
   3.750   0.7012   0.01499   0.00684  -0.0191   0.3562   1.0000
   4.000   0.7271   0.01529   0.00719  -0.0188   0.3519   1.0000
   4.250   0.7533   0.01555   0.00745  -0.0185   0.3473   1.0000
   4.500   0.7796   0.01582   0.00765  -0.0182   0.3433   1.0000
   4.750   0.8060   0.01625   0.00794  -0.0180   0.3397   1.0000
   5.000   0.8319   0.01656   0.00836  -0.0178   0.3358   1.0000
   5.250   0.8581   0.01688   0.00871  -0.0176   0.3318   1.0000
   5.500   0.8846   0.01718   0.00898  -0.0174   0.3281   1.0000
   5.750   0.9112   0.01757   0.00925  -0.0172   0.3248   1.0000
   6.000   0.9368   0.01800   0.00977  -0.0170   0.3211   1.0000
   6.250   0.9625   0.01839   0.01025  -0.0169   0.3174   1.0000
   6.500   0.9887   0.01874   0.01061  -0.0167   0.3139   1.0000
   6.750   1.0152   0.01908   0.01089  -0.0166   0.3108   1.0000
   7.000   1.0414   0.01963   0.01139  -0.0165   0.3076   1.0000
   7.250   1.0659   0.02007   0.01200  -0.0163   0.3040   1.0000
   7.500   1.0910   0.02052   0.01253  -0.0161   0.3006   1.0000
   7.750   1.1169   0.02090   0.01292  -0.0159   0.2974   1.0000
   8.000   1.1434   0.02130   0.01325  -0.0159   0.2945   1.0000
   8.250   1.1682   0.02193   0.01393  -0.0157   0.2914   1.0000
   8.500   1.1913   0.02249   0.01468  -0.0154   0.2878   1.0000
   8.750   1.2154   0.02301   0.01528  -0.0152   0.2846   1.0000
   9.000   1.2408   0.02341   0.01569  -0.0151   0.2815   1.0000
   9.250   1.2674   0.02384   0.01605  -0.0150   0.2787   1.0000
   9.500   1.2898   0.02460   0.01694  -0.0148   0.2756   1.0000
   9.750   1.3107   0.02531   0.01785  -0.0144   0.2722   1.0000
  10.000   1.3333   0.02587   0.01851  -0.0140   0.2689   1.0000
  10.250   1.3583   0.02624   0.01888  -0.0139   0.2660   1.0000
  10.500   1.3852   0.02675   0.01932  -0.0139   0.2632   1.0000
  10.750   1.4033   0.02768   0.02047  -0.0134   0.2601   1.0000
  11.000   1.4207   0.02849   0.02149  -0.0127   0.2565   1.0000
  11.250   1.4417   0.02903   0.02211  -0.0123   0.2532   1.0000
  11.500   1.4668   0.02938   0.02245  -0.0121   0.2504   1.0000
  11.750   1.4926   0.03006   0.02308  -0.0122   0.2475   1.0000
  12.000   1.5017   0.03118   0.02451  -0.0109   0.2440   1.0000
  12.250   1.5153   0.03205   0.02557  -0.0100   0.2405   1.0000
  12.500   1.5359   0.03246   0.02601  -0.0095   0.2374   1.0000
  12.750   1.5647   0.03266   0.02612  -0.0096   0.2345   1.0000
  13.000   1.5729   0.03394   0.02760  -0.0084   0.2313   1.0000
  13.250   1.5723   0.03534   0.02926  -0.0065   0.2279   1.0000
  13.500   1.5788   0.03621   0.03024  -0.0050   0.2248   1.0000
  13.750   1.6022   0.03636   0.03036  -0.0046   0.2218   1.0000
  14.000   1.6241   0.03695   0.03094  -0.0043   0.2186   1.0000
  14.250   1.5971   0.03954   0.03381  -0.0014   0.2162   1.0000
  14.500   1.5783   0.04241   0.03688  -0.0004   0.2132   1.0000
  14.750   1.5823   0.04389   0.03844  -0.0001   0.2101   1.0000
  15.000   1.6250   0.04254   0.03696   0.0003   0.2067   1.0000
  15.250   1.6020   0.04634   0.04098   0.0004   0.2040   1.0000
  15.500   1.5505   0.05350   0.04844  -0.0014   0.2011   1.0000
  15.750   1.5155   0.05990   0.05502  -0.0037   0.1977   1.0000
  16.000   1.5765   0.05541   0.05040  -0.0014   0.1944   1.0000
  16.250   1.5683   0.05890   0.05398  -0.0024   0.1912   1.0000
  16.500   1.0317   0.15528   0.15065  -0.0511   0.1547   1.0000
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