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MH 82 13.31% (mh82-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 82 13.31% (mh82-il)
Reynolds number: 200,000
Max Cl/Cd: 61.71 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh82-il-200000-n5.txt
Download as CSV file: xf-mh82-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3838   0.08747   0.08365  -0.0003   0.6889   0.0184
  -8.250  -0.3727   0.08633   0.08245  -0.0003   0.6728   0.0193
  -7.750  -0.4143   0.06824   0.06438  -0.0134   0.6628   0.0149
  -7.500  -0.4146   0.06337   0.05942  -0.0173   0.6525   0.0148
  -7.250  -0.4136   0.05807   0.05398  -0.0207   0.6435   0.0146
  -7.000  -0.4121   0.05186   0.04756  -0.0237   0.6350   0.0143
  -6.750  -0.4104   0.04494   0.04026  -0.0256   0.6275   0.0139
  -6.500  -0.4066   0.03777   0.03250  -0.0265   0.6201   0.0134
  -6.250  -0.3955   0.03238   0.02640  -0.0262   0.6113   0.0131
  -6.000  -0.3776   0.02880   0.02223  -0.0256   0.6013   0.0130
  -5.750  -0.3561   0.02637   0.01929  -0.0249   0.5912   0.0130
  -5.500  -0.3324   0.02450   0.01703  -0.0243   0.5800   0.0131
  -5.250  -0.3076   0.02298   0.01517  -0.0238   0.5697   0.0133
  -5.000  -0.2820   0.02169   0.01358  -0.0232   0.5591   0.0135
  -4.750  -0.2558   0.02056   0.01221  -0.0227   0.5486   0.0138
  -4.500  -0.2295   0.01958   0.01100  -0.0222   0.5388   0.0142
  -4.250  -0.2027   0.01869   0.00992  -0.0217   0.5284   0.0147
  -4.000  -0.1761   0.01794   0.00903  -0.0213   0.5189   0.0152
  -3.750  -0.1495   0.01733   0.00835  -0.0209   0.5090   0.0158
  -3.500  -0.1224   0.01685   0.00776  -0.0206   0.4997   0.0171
  -3.250  -0.0953   0.01639   0.00720  -0.0202   0.4903   0.0187
  -3.000  -0.0680   0.01599   0.00673  -0.0200   0.4813   0.0207
  -2.750  -0.0407   0.01556   0.00619  -0.0196   0.4728   0.0226
  -2.500  -0.0131   0.01518   0.00574  -0.0193   0.4643   0.0254
  -2.250   0.0144   0.01484   0.00532  -0.0190   0.4560   0.0311
  -2.000   0.0418   0.01442   0.00495  -0.0188   0.4476   0.0445
  -1.750   0.0686   0.01397   0.00466  -0.0185   0.4397   0.0893
  -1.500   0.0958   0.01362   0.00450  -0.0184   0.4323   0.1453
  -1.250   0.1225   0.01326   0.00437  -0.0182   0.4249   0.2158
  -1.000   0.1483   0.01278   0.00426  -0.0180   0.4180   0.3246
  -0.750   0.1726   0.01218   0.00419  -0.0174   0.4107   0.4747
  -0.500   0.1942   0.01159   0.00416  -0.0159   0.4044   0.6479
  -0.250   0.2160   0.01120   0.00428  -0.0135   0.3977   0.8102
   0.000   0.2487   0.01123   0.00431  -0.0136   0.3910   0.8982
   0.250   0.2865   0.01132   0.00429  -0.0150   0.3844   0.9402
   0.500   0.3270   0.01142   0.00426  -0.0172   0.3771   0.9648
   0.750   0.3685   0.01155   0.00421  -0.0198   0.3706   0.9835
   1.000   0.4189   0.01162   0.00416  -0.0242   0.3630   0.9997
   1.250   0.4442   0.01176   0.00417  -0.0237   0.3580   1.0000
   1.500   0.4691   0.01191   0.00421  -0.0231   0.3534   1.0000
   1.750   0.4943   0.01205   0.00428  -0.0226   0.3482   1.0000
   2.000   0.5194   0.01221   0.00434  -0.0220   0.3432   1.0000
   2.250   0.5445   0.01240   0.00441  -0.0214   0.3388   1.0000
   2.500   0.5700   0.01255   0.00453  -0.0209   0.3340   1.0000
   2.750   0.5955   0.01273   0.00464  -0.0204   0.3297   1.0000
   3.000   0.6209   0.01294   0.00476  -0.0200   0.3259   1.0000
   3.250   0.6466   0.01315   0.00490  -0.0195   0.3220   1.0000
   3.500   0.6725   0.01334   0.00507  -0.0191   0.3177   1.0000
   3.750   0.6985   0.01355   0.00523  -0.0188   0.3135   1.0000
   4.000   0.7243   0.01378   0.00539  -0.0184   0.3100   1.0000
   4.250   0.7503   0.01403   0.00559  -0.0181   0.3067   1.0000
   4.500   0.7766   0.01425   0.00582  -0.0179   0.3030   1.0000
   4.750   0.8028   0.01448   0.00604  -0.0176   0.2993   1.0000
   5.000   0.8288   0.01474   0.00625  -0.0173   0.2958   1.0000
   5.250   0.8546   0.01504   0.00646  -0.0171   0.2928   1.0000
   5.500   0.8810   0.01529   0.00677  -0.0169   0.2896   1.0000
   5.750   0.9071   0.01555   0.00706  -0.0167   0.2863   1.0000
   6.000   0.9331   0.01583   0.00733  -0.0165   0.2830   1.0000
   6.250   0.9589   0.01613   0.00760  -0.0163   0.2799   1.0000
   6.500   0.9845   0.01646   0.00790  -0.0161   0.2771   1.0000
   6.750   1.0104   0.01676   0.00827  -0.0159   0.2742   1.0000
   7.000   1.0361   0.01708   0.00864  -0.0157   0.2711   1.0000
   7.250   1.0615   0.01739   0.00898  -0.0155   0.2680   1.0000
   7.500   1.0867   0.01773   0.00931  -0.0153   0.2651   1.0000
   7.750   1.1117   0.01812   0.00966  -0.0151   0.2625   1.0000
   8.000   1.1368   0.01848   0.01012  -0.0149   0.2598   1.0000
   8.250   1.1615   0.01885   0.01058  -0.0147   0.2569   1.0000
   8.500   1.1860   0.01923   0.01101  -0.0145   0.2539   1.0000
   8.750   1.2102   0.01961   0.01141  -0.0142   0.2510   1.0000
   9.000   1.2342   0.02003   0.01183  -0.0139   0.2486   1.0000
   9.250   1.2578   0.02049   0.01237  -0.0137   0.2461   1.0000
   9.500   1.2810   0.02094   0.01294  -0.0134   0.2431   1.0000
   9.750   1.3038   0.02138   0.01348  -0.0130   0.2401   1.0000
  10.000   1.3263   0.02184   0.01398  -0.0127   0.2373   1.0000
  10.250   1.3485   0.02232   0.01448  -0.0123   0.2349   1.0000
  10.500   1.3702   0.02286   0.01507  -0.0119   0.2325   1.0000
  10.750   1.3903   0.02342   0.01580  -0.0114   0.2295   1.0000
  11.000   1.4100   0.02399   0.01648  -0.0108   0.2264   1.0000
  11.250   1.4291   0.02456   0.01714  -0.0102   0.2237   1.0000
  11.500   1.4477   0.02514   0.01774  -0.0096   0.2211   1.0000
  11.750   1.4652   0.02579   0.01845  -0.0088   0.2185   1.0000
  12.000   1.4791   0.02658   0.01942  -0.0079   0.2155   1.0000
  12.250   1.4899   0.02738   0.02035  -0.0065   0.2126   1.0000
  12.500   1.4988   0.02825   0.02132  -0.0052   0.2098   1.0000
  12.750   1.5088   0.02918   0.02228  -0.0042   0.2073   1.0000
  13.000   1.5173   0.03031   0.02348  -0.0033   0.2047   1.0000
  13.250   1.5215   0.03185   0.02520  -0.0027   0.2017   1.0000
  13.500   1.5260   0.03347   0.02696  -0.0023   0.1987   1.0000
  13.750   1.5309   0.03513   0.02871  -0.0021   0.1958   1.0000
  14.000   1.5376   0.03669   0.03028  -0.0019   0.1931   1.0000
  14.250   1.5376   0.03902   0.03278  -0.0021   0.1902   1.0000
  14.500   1.5348   0.04175   0.03568  -0.0026   0.1869   1.0000
  14.750   1.5334   0.04442   0.03846  -0.0031   0.1838   1.0000
  15.000   1.5346   0.04681   0.04089  -0.0035   0.1810   1.0000
  15.250   1.5298   0.05001   0.04420  -0.0044   0.1780   1.0000
  15.500   1.5175   0.05427   0.04866  -0.0058   0.1746   1.0000
  15.750   1.5073   0.05837   0.05288  -0.0073   0.1712   1.0000
  16.000   1.5055   0.06139   0.05592  -0.0082   0.1683   1.0000
  16.250   1.4918   0.06629   0.06097  -0.0102   0.1651   1.0000
  16.500   1.4672   0.07298   0.06784  -0.0131   0.1614   1.0000
  16.750   1.4556   0.07794   0.07288  -0.0153   0.1577   1.0000
  17.000   1.4580   0.08073   0.07566  -0.0163   0.1546   1.0000
  17.250   1.4127   0.09133   0.08651  -0.0213   0.1504   1.0000
  17.500   1.3916   0.09827   0.09354  -0.0246   0.1463   1.0000
  17.750   1.4082   0.09886   0.09409  -0.0247   0.1433   1.0000
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