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MH 83 13.29% (mh83-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: MH 83 13.29% (mh83-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123.91 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh83-il-1000000-n5.txt
Download as CSV file: xf-mh83-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 83  13.29%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6117   0.03272   0.02931  -0.0583   0.6221   0.0078
  -9.500  -0.5982   0.02859   0.02482  -0.0615   0.6125   0.0079
  -9.250  -0.5784   0.02617   0.02212  -0.0628   0.6016   0.0079
  -9.000  -0.5563   0.02427   0.01997  -0.0637   0.5911   0.0079
  -8.750  -0.5325   0.02276   0.01823  -0.0642   0.5800   0.0080
  -8.500  -0.5101   0.02053   0.01568  -0.0649   0.5701   0.0081
  -8.250  -0.4852   0.01911   0.01402  -0.0652   0.5597   0.0082
  -8.000  -0.4591   0.01805   0.01280  -0.0653   0.5492   0.0083
  -7.750  -0.4323   0.01723   0.01182  -0.0654   0.5393   0.0084
  -7.500  -0.4051   0.01654   0.01099  -0.0654   0.5287   0.0084
  -7.250  -0.3776   0.01591   0.01024  -0.0654   0.5191   0.0085
  -6.750  -0.3218   0.01483   0.00892  -0.0653   0.4997   0.0087
  -6.500  -0.2936   0.01435   0.00833  -0.0653   0.4899   0.0088
  -6.250  -0.2653   0.01388   0.00776  -0.0652   0.4810   0.0089
  -6.000  -0.2369   0.01345   0.00722  -0.0652   0.4729   0.0091
  -5.750  -0.2083   0.01305   0.00673  -0.0651   0.4641   0.0092
  -5.500  -0.1797   0.01271   0.00629  -0.0651   0.4552   0.0094
  -5.250  -0.1509   0.01239   0.00589  -0.0650   0.4462   0.0096
  -5.000  -0.1221   0.01210   0.00550  -0.0650   0.4386   0.0099
  -4.750  -0.0931   0.01180   0.00513  -0.0649   0.4313   0.0101
  -4.250  -0.0351   0.01129   0.00447  -0.0648   0.4168   0.0104
  -4.000  -0.0060   0.01102   0.00411  -0.0648   0.4083   0.0106
  -3.750   0.0231   0.01070   0.00374  -0.0648   0.4012   0.0109
  -3.500   0.0523   0.01051   0.00349  -0.0648   0.3937   0.0113
  -3.250   0.0815   0.01035   0.00328  -0.0648   0.3877   0.0116
  -3.000   0.1108   0.01020   0.00309  -0.0648   0.3814   0.0120
  -2.750   0.1400   0.01008   0.00291  -0.0648   0.3749   0.0123
  -2.500   0.1694   0.00995   0.00274  -0.0647   0.3694   0.0128
  -2.250   0.1986   0.00986   0.00260  -0.0647   0.3628   0.0131
  -2.000   0.2279   0.00976   0.00245  -0.0647   0.3563   0.0137
  -1.750   0.2572   0.00966   0.00233  -0.0647   0.3508   0.0146
  -1.500   0.2865   0.00960   0.00223  -0.0647   0.3452   0.0158
  -1.250   0.3158   0.00955   0.00214  -0.0647   0.3401   0.0174
  -1.000   0.3451   0.00948   0.00207  -0.0647   0.3358   0.0202
  -0.750   0.3744   0.00938   0.00199  -0.0647   0.3308   0.0322
  -0.250   0.4327   0.00920   0.00193  -0.0648   0.3211   0.0840
   0.000   0.4619   0.00910   0.00192  -0.0649   0.3165   0.1156
   0.250   0.4910   0.00902   0.00192  -0.0650   0.3121   0.1581
   0.500   0.5201   0.00895   0.00195  -0.0651   0.3082   0.2018
   0.750   0.5492   0.00888   0.00198  -0.0652   0.3052   0.2439
   1.000   0.5783   0.00881   0.00202  -0.0653   0.3016   0.2910
   1.250   0.6073   0.00879   0.00207  -0.0654   0.2975   0.3306
   1.500   0.6362   0.00881   0.00213  -0.0654   0.2931   0.3684
   1.750   0.6652   0.00876   0.00219  -0.0655   0.2905   0.4151
   2.000   0.6941   0.00871   0.00226  -0.0656   0.2876   0.4707
   2.250   0.7229   0.00867   0.00235  -0.0657   0.2846   0.5323
   2.500   0.7512   0.00855   0.00246  -0.0657   0.2815   0.6339
   2.750   0.7785   0.00838   0.00259  -0.0655   0.2781   0.7575
   3.000   0.8050   0.00798   0.00266  -0.0648   0.2759   1.0000
   3.250   0.8339   0.00809   0.00273  -0.0649   0.2733   1.0000
   3.500   0.8627   0.00821   0.00282  -0.0649   0.2706   1.0000
   3.750   0.8914   0.00834   0.00292  -0.0649   0.2679   1.0000
   4.000   0.9200   0.00849   0.00303  -0.0650   0.2652   1.0000
   4.250   0.9485   0.00865   0.00315  -0.0650   0.2623   1.0000
   4.500   0.9772   0.00876   0.00325  -0.0651   0.2605   1.0000
   4.750   1.0058   0.00889   0.00336  -0.0651   0.2582   1.0000
   5.000   1.0342   0.00903   0.00348  -0.0652   0.2560   1.0000
   5.250   1.0625   0.00918   0.00361  -0.0652   0.2537   1.0000
   5.500   1.0907   0.00935   0.00376  -0.0653   0.2511   1.0000
   5.750   1.1187   0.00953   0.00392  -0.0653   0.2481   1.0000
   6.000   1.1469   0.00968   0.00406  -0.0654   0.2464   1.0000
   6.250   1.1750   0.00982   0.00421  -0.0654   0.2447   1.0000
   6.500   1.2030   0.00997   0.00437  -0.0654   0.2429   1.0000
   6.750   1.2309   0.01014   0.00453  -0.0655   0.2407   1.0000
   7.000   1.2586   0.01032   0.00471  -0.0655   0.2381   1.0000
   7.250   1.2860   0.01053   0.00490  -0.0655   0.2354   1.0000
   7.500   1.3133   0.01075   0.00512  -0.0655   0.2329   1.0000
   7.750   1.3408   0.01091   0.00530  -0.0656   0.2317   1.0000
   8.000   1.3683   0.01108   0.00549  -0.0656   0.2300   1.0000
   8.250   1.3955   0.01127   0.00569  -0.0656   0.2277   1.0000
   8.500   1.4225   0.01148   0.00590  -0.0656   0.2252   1.0000
   8.750   1.4492   0.01170   0.00614  -0.0655   0.2230   1.0000
   9.000   1.4755   0.01196   0.00640  -0.0655   0.2204   1.0000
   9.250   1.5019   0.01220   0.00665  -0.0654   0.2181   1.0000
   9.500   1.5285   0.01240   0.00688  -0.0654   0.2163   1.0000
   9.750   1.5548   0.01262   0.00713  -0.0653   0.2141   1.0000
  10.000   1.5807   0.01287   0.00740  -0.0653   0.2114   1.0000
  10.250   1.6060   0.01316   0.00770  -0.0651   0.2085   1.0000
  10.500   1.6308   0.01350   0.00804  -0.0649   0.2054   1.0000
  10.750   1.6562   0.01374   0.00832  -0.0648   0.2033   1.0000
  11.000   1.6813   0.01401   0.00863  -0.0647   0.2008   1.0000
  11.250   1.7056   0.01432   0.00896  -0.0644   0.1975   1.0000
  11.500   1.7289   0.01470   0.00935  -0.0641   0.1941   1.0000
  11.750   1.7520   0.01508   0.00974  -0.0638   0.1907   1.0000
  12.000   1.7753   0.01541   0.01012  -0.0635   0.1871   1.0000
  12.250   1.7969   0.01585   0.01057  -0.0630   0.1824   1.0000
  12.500   1.8171   0.01636   0.01108  -0.0623   0.1780   1.0000
  12.750   1.8376   0.01680   0.01155  -0.0617   0.1735   1.0000
  13.000   1.8547   0.01742   0.01217  -0.0608   0.1679   1.0000
  13.250   1.8713   0.01801   0.01278  -0.0598   0.1636   1.0000
  13.500   1.8845   0.01862   0.01343  -0.0582   0.1592   1.0000
  13.750   1.8876   0.01955   0.01438  -0.0556   0.1547   1.0000
  14.000   1.8937   0.02053   0.01541  -0.0537   0.1509   1.0000
  14.250   1.8943   0.02205   0.01693  -0.0519   0.1439   1.0000
  14.500   1.8959   0.02372   0.01863  -0.0506   0.1383   1.0000
  14.750   1.8917   0.02604   0.02095  -0.0495   0.1307   1.0000
  15.000   1.8907   0.02830   0.02325  -0.0488   0.1251   1.0000
  15.250   1.8823   0.03140   0.02637  -0.0483   0.1186   1.0000
  15.500   1.8777   0.03432   0.02935  -0.0481   0.1137   1.0000
  15.750   1.8646   0.03826   0.03333  -0.0482   0.1081   1.0000
  16.000   1.8521   0.04230   0.03743  -0.0486   0.1030   1.0000
  16.250   1.8397   0.04648   0.04168  -0.0491   0.0995   1.0000
  16.500   1.8205   0.05161   0.04689  -0.0501   0.0956   1.0000
  16.750   1.7989   0.05730   0.05265  -0.0514   0.0907   1.0000
  17.000   1.7795   0.06300   0.05843  -0.0530   0.0877   1.0000
  17.250   1.7608   0.06879   0.06432  -0.0548   0.0854   1.0000
  17.500   1.7418   0.07484   0.07046  -0.0568   0.0821   1.0000
  17.750   1.7212   0.08122   0.07693  -0.0590   0.0794   1.0000
  18.250   1.6800   0.09461   0.09050  -0.0641   0.0741   1.0000
  18.500   1.6607   0.10133   0.09730  -0.0669   0.0712   1.0000
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