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MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 32 8.7% (mh32-il)
Reynolds number: 200,000
Max Cl/Cd: 67.16 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh32-il-200000-n5.txt
Download as CSV file: xf-mh32-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 32  8.7%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3434   0.09723   0.09384  -0.0245   1.0000   0.0113
  -9.500  -0.4215   0.10167   0.09802  -0.0224   1.0000   0.0126
  -9.250  -0.4195   0.09783   0.09421  -0.0239   1.0000   0.0116
  -8.750  -0.4206   0.08777   0.08423  -0.0283   1.0000   0.0085
  -8.500  -0.4206   0.08417   0.08067  -0.0297   1.0000   0.0083
  -8.250  -0.4227   0.08019   0.07675  -0.0314   1.0000   0.0081
  -8.000  -0.4257   0.07653   0.07315  -0.0330   1.0000   0.0080
  -7.750  -0.4333   0.07282   0.06952  -0.0343   1.0000   0.0078
  -7.500  -0.4415   0.06893   0.06570  -0.0365   1.0000   0.0077
  -7.250  -0.4487   0.06421   0.06101  -0.0394   1.0000   0.0076
  -7.000  -0.4553   0.06005   0.05683  -0.0405   1.0000   0.0074
  -6.750  -0.4624   0.05561   0.05233  -0.0408   1.0000   0.0073
  -6.500  -0.4398   0.04751   0.04394  -0.0485   0.9932   0.0070
  -6.250  -0.4176   0.03991   0.03590  -0.0535   0.9862   0.0066
  -6.000  -0.3918   0.03270   0.02805  -0.0571   0.9810   0.0063
  -5.750  -0.3672   0.02734   0.02197  -0.0584   0.9746   0.0060
  -5.500  -0.3365   0.02366   0.01764  -0.0599   0.9706   0.0060
  -5.250  -0.3056   0.02110   0.01460  -0.0608   0.9666   0.0062
  -5.000  -0.2764   0.01920   0.01234  -0.0612   0.9613   0.0065
  -4.750  -0.2443   0.01763   0.01050  -0.0621   0.9575   0.0069
  -4.500  -0.2135   0.01635   0.00901  -0.0626   0.9531   0.0075
  -4.250  -0.1845   0.01557   0.00804  -0.0628   0.9472   0.0090
  -4.000  -0.1534   0.01468   0.00711  -0.0638   0.9430   0.0127
  -3.750  -0.1255   0.01391   0.00620  -0.0636   0.9366   0.0156
  -3.500  -0.0962   0.01308   0.00528  -0.0638   0.9309   0.0263
  -3.250  -0.0682   0.01232   0.00465  -0.0639   0.9247   0.0615
  -3.000  -0.0410   0.01167   0.00426  -0.0640   0.9178   0.1283
  -2.500   0.0124   0.01060   0.00374  -0.0638   0.9033   0.3022
  -2.250   0.0377   0.01015   0.00356  -0.0634   0.8951   0.3934
  -2.000   0.0637   0.00972   0.00341  -0.0629   0.8877   0.4876
  -1.750   0.0873   0.00936   0.00332  -0.0618   0.8782   0.5774
  -1.500   0.1115   0.00904   0.00321  -0.0607   0.8697   0.6606
  -1.250   0.1355   0.00877   0.00314  -0.0593   0.8610   0.7377
  -1.000   0.1592   0.00857   0.00309  -0.0578   0.8509   0.8082
  -0.750   0.1877   0.00843   0.00301  -0.0572   0.8414   0.8733
  -0.500   0.2267   0.00832   0.00286  -0.0590   0.8325   0.9289
  -0.250   0.2691   0.00825   0.00272  -0.0618   0.8213   0.9690
   0.000   0.3109   0.00820   0.00257  -0.0647   0.8086   0.9980
   0.250   0.3366   0.00822   0.00248  -0.0642   0.7937   1.0000
   0.500   0.3608   0.00825   0.00240  -0.0633   0.7775   1.0000
   0.750   0.3854   0.00829   0.00235  -0.0625   0.7599   1.0000
   1.000   0.4102   0.00835   0.00231  -0.0617   0.7417   1.0000
   1.250   0.4351   0.00843   0.00229  -0.0609   0.7226   1.0000
   1.500   0.4602   0.00853   0.00230  -0.0602   0.7018   1.0000
   1.750   0.4852   0.00865   0.00231  -0.0595   0.6806   1.0000
   2.000   0.5102   0.00879   0.00234  -0.0588   0.6580   1.0000
   2.250   0.5353   0.00895   0.00240  -0.0582   0.6349   1.0000
   2.500   0.5602   0.00914   0.00247  -0.0575   0.6115   1.0000
   2.750   0.5850   0.00935   0.00261  -0.0569   0.5876   1.0000
   3.000   0.6098   0.00957   0.00274  -0.0562   0.5629   1.0000
   3.250   0.6346   0.00980   0.00289  -0.0556   0.5380   1.0000
   3.500   0.6592   0.01005   0.00306  -0.0550   0.5122   1.0000
   3.750   0.6837   0.01032   0.00327  -0.0543   0.4858   1.0000
   4.000   0.7081   0.01061   0.00348  -0.0537   0.4588   1.0000
   4.250   0.7322   0.01092   0.00372  -0.0531   0.4311   1.0000
   4.500   0.7562   0.01126   0.00398  -0.0524   0.4029   1.0000
   4.750   0.7799   0.01162   0.00426  -0.0518   0.3740   1.0000
   5.000   0.8035   0.01201   0.00461  -0.0511   0.3447   1.0000
   5.500   0.8499   0.01288   0.00533  -0.0497   0.2859   1.0000
   5.750   0.8729   0.01335   0.00573  -0.0490   0.2573   1.0000
   6.000   0.8956   0.01385   0.00618  -0.0483   0.2298   1.0000
   6.250   0.9181   0.01438   0.00665  -0.0476   0.2021   1.0000
   6.500   0.9400   0.01498   0.00721  -0.0468   0.1724   1.0000
   6.750   0.9611   0.01566   0.00778  -0.0460   0.1415   1.0000
   7.000   0.9820   0.01637   0.00839  -0.0451   0.1144   1.0000
   7.250   1.0034   0.01703   0.00904  -0.0443   0.0939   1.0000
   7.500   1.0237   0.01780   0.00976  -0.0433   0.0752   1.0000
   7.750   1.0435   0.01862   0.01056  -0.0423   0.0560   1.0000
   8.000   1.0618   0.01959   0.01148  -0.0411   0.0406   1.0000
   8.250   1.0794   0.02062   0.01248  -0.0398   0.0282   1.0000
   8.500   1.0963   0.02170   0.01365  -0.0384   0.0195   1.0000
   8.750   1.1129   0.02276   0.01482  -0.0369   0.0138   1.0000
   9.000   1.1270   0.02405   0.01621  -0.0351   0.0098   1.0000
   9.250   1.1405   0.02531   0.01764  -0.0333   0.0081   1.0000
   9.500   1.1504   0.02685   0.01931  -0.0311   0.0069   1.0000
   9.750   1.1535   0.02881   0.02145  -0.0280   0.0062   1.0000
  10.000   1.1592   0.03037   0.02320  -0.0253   0.0059   1.0000
  10.250   1.1634   0.03211   0.02513  -0.0226   0.0056   1.0000
  10.500   1.1669   0.03401   0.02722  -0.0201   0.0054   1.0000
  10.750   1.1689   0.03616   0.02958  -0.0178   0.0052   1.0000
  11.000   1.1717   0.03819   0.03180  -0.0159   0.0048   1.0000
  11.250   1.1737   0.04025   0.03405  -0.0143   0.0045   1.0000
  11.500   1.1764   0.04210   0.03604  -0.0132   0.0040   1.0000
  11.750   1.1757   0.04448   0.03857  -0.0123   0.0038   1.0000
  12.000   1.1704   0.04750   0.04175  -0.0118   0.0035   1.0000
  12.250   1.1610   0.05138   0.04585  -0.0117   0.0033   1.0000
  12.500   1.1523   0.05547   0.05021  -0.0122   0.0032   1.0000
  12.750   1.1424   0.06007   0.05503  -0.0132   0.0033   1.0000
  13.000   1.1319   0.06505   0.06023  -0.0152   0.0031   1.0000
  13.250   1.1233   0.07013   0.06552  -0.0176   0.0030   1.0000
  13.500   1.1097   0.07641   0.07202  -0.0208   0.0029   1.0000
  13.750   1.0914   0.08391   0.07968  -0.0249   0.0031   1.0000
  14.000   1.0800   0.09078   0.08674  -0.0291   0.0030   1.0000
  14.250   1.0594   0.09973   0.09584  -0.0342   0.0032   1.0000
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