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MH 115 11.06% (mh115-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: MH 115 11.06% (mh115-il)
Reynolds number: 1,000,000
Max Cl/Cd: 140.37 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh115-il-1000000-n5.txt
Download as CSV file: xf-mh115-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 115  11.06%                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1985   0.02469   0.02196  -0.1574   0.8764   0.0033
  -8.500  -0.1855   0.02068   0.01746  -0.1599   0.8639   0.0033
  -8.250  -0.1659   0.01824   0.01464  -0.1609   0.8538   0.0033
  -8.000  -0.1432   0.01660   0.01270  -0.1615   0.8441   0.0033
  -7.750  -0.1191   0.01523   0.01106  -0.1618   0.8351   0.0033
  -7.250  -0.0681   0.01328   0.00867  -0.1622   0.8176   0.0033
  -7.000  -0.0418   0.01255   0.00775  -0.1623   0.8092   0.0033
  -6.750  -0.0150   0.01187   0.00692  -0.1625   0.8006   0.0033
  -6.500   0.0119   0.01132   0.00623  -0.1625   0.7925   0.0034
  -6.250   0.0392   0.01082   0.00559  -0.1626   0.7842   0.0034
  -6.000   0.0666   0.01040   0.00505  -0.1627   0.7765   0.0034
  -5.750   0.0942   0.01003   0.00457  -0.1627   0.7683   0.0035
  -5.500   0.1220   0.00969   0.00413  -0.1628   0.7610   0.0036
  -5.250   0.1497   0.00939   0.00374  -0.1628   0.7530   0.0036
  -5.000   0.1777   0.00906   0.00331  -0.1629   0.7459   0.0039
  -4.750   0.2057   0.00882   0.00299  -0.1629   0.7381   0.0042
  -4.500   0.2337   0.00863   0.00274  -0.1629   0.7311   0.0048
  -4.250   0.2618   0.00847   0.00252  -0.1630   0.7234   0.0054
  -4.000   0.2898   0.00831   0.00230  -0.1630   0.7161   0.0070
  -3.750   0.3179   0.00815   0.00212  -0.1630   0.7084   0.0108
  -3.500   0.3458   0.00803   0.00199  -0.1630   0.7010   0.0160
  -3.250   0.3739   0.00794   0.00187  -0.1631   0.6930   0.0209
  -3.000   0.4018   0.00784   0.00176  -0.1631   0.6857   0.0277
  -2.750   0.4300   0.00771   0.00166  -0.1632   0.6778   0.0423
  -2.500   0.4579   0.00759   0.00158  -0.1632   0.6703   0.0612
  -2.250   0.4860   0.00751   0.00151  -0.1633   0.6622   0.0794
  -2.000   0.5139   0.00745   0.00146  -0.1633   0.6547   0.0960
  -1.750   0.5419   0.00738   0.00142  -0.1634   0.6464   0.1176
  -1.250   0.5978   0.00728   0.00137  -0.1635   0.6302   0.1697
  -1.000   0.6257   0.00722   0.00137  -0.1635   0.6223   0.2055
  -0.750   0.6534   0.00719   0.00137  -0.1635   0.6135   0.2377
  -0.500   0.6813   0.00716   0.00139  -0.1636   0.6052   0.2696
   0.000   0.7366   0.00713   0.00144  -0.1636   0.5869   0.3398
   0.250   0.7641   0.00713   0.00149  -0.1636   0.5778   0.3796
   0.500   0.7915   0.00713   0.00155  -0.1635   0.5676   0.4201
   0.750   0.8190   0.00714   0.00161  -0.1635   0.5579   0.4609
   1.000   0.8461   0.00717   0.00168  -0.1634   0.5474   0.5038
   1.250   0.8732   0.00721   0.00177  -0.1633   0.5363   0.5450
   1.500   0.9003   0.00724   0.00186  -0.1632   0.5251   0.5889
   1.750   0.9271   0.00730   0.00196  -0.1631   0.5134   0.6314
   2.000   0.9535   0.00737   0.00208  -0.1629   0.5010   0.6757
   2.250   0.9797   0.00745   0.00220  -0.1626   0.4883   0.7206
   2.500   1.0055   0.00752   0.00234  -0.1622   0.4750   0.7692
   2.750   1.0305   0.00759   0.00248  -0.1616   0.4613   0.8219
   3.000   1.0521   0.00761   0.00262  -0.1602   0.4480   0.8925
   3.250   1.0738   0.00765   0.00269  -0.1589   0.4338   1.0000
   3.500   1.0993   0.00787   0.00284  -0.1585   0.4188   1.0000
   3.750   1.1247   0.00809   0.00299  -0.1581   0.4043   1.0000
   4.000   1.1497   0.00833   0.00316  -0.1577   0.3890   1.0000
   4.250   1.1746   0.00858   0.00333  -0.1572   0.3740   1.0000
   4.500   1.1992   0.00884   0.00353  -0.1567   0.3588   1.0000
   4.750   1.2233   0.00912   0.00373  -0.1561   0.3424   1.0000
   5.000   1.2471   0.00941   0.00394  -0.1554   0.3265   1.0000
   5.250   1.2707   0.00972   0.00418  -0.1547   0.3104   1.0000
   5.500   1.2937   0.01005   0.00442  -0.1540   0.2939   1.0000
   5.750   1.3165   0.01037   0.00468  -0.1532   0.2783   1.0000
   6.000   1.3397   0.01067   0.00493  -0.1524   0.2655   1.0000
   6.250   1.3621   0.01100   0.00520  -0.1516   0.2515   1.0000
   6.500   1.3842   0.01134   0.00548  -0.1506   0.2382   1.0000
   6.750   1.4059   0.01168   0.00578  -0.1497   0.2259   1.0000
   7.000   1.4267   0.01205   0.00610  -0.1485   0.2125   1.0000
   7.250   1.4473   0.01242   0.00643  -0.1473   0.2011   1.0000
   7.500   1.4662   0.01280   0.00677  -0.1458   0.1897   1.0000
   7.750   1.4841   0.01321   0.00713  -0.1442   0.1773   1.0000
   8.000   1.5020   0.01360   0.00749  -0.1425   0.1670   1.0000
   8.250   1.5192   0.01403   0.00789  -0.1407   0.1568   1.0000
   8.500   1.5351   0.01452   0.00834  -0.1388   0.1453   1.0000
   8.750   1.5508   0.01503   0.00882  -0.1368   0.1348   1.0000
   9.000   1.5655   0.01559   0.00934  -0.1348   0.1228   1.0000
   9.250   1.5780   0.01629   0.00996  -0.1324   0.1087   1.0000
   9.500   1.5894   0.01704   0.01065  -0.1300   0.0946   1.0000
   9.750   1.6019   0.01777   0.01133  -0.1278   0.0843   1.0000
  10.000   1.6136   0.01854   0.01207  -0.1255   0.0744   1.0000
  10.250   1.6252   0.01934   0.01285  -0.1233   0.0656   1.0000
  10.500   1.6361   0.02021   0.01369  -0.1211   0.0576   1.0000
  10.750   1.6457   0.02118   0.01463  -0.1188   0.0497   1.0000
  11.000   1.6545   0.02224   0.01567  -0.1165   0.0422   1.0000
  11.250   1.6627   0.02338   0.01679  -0.1143   0.0350   1.0000
  11.500   1.6691   0.02469   0.01808  -0.1119   0.0274   1.0000
  11.750   1.6744   0.02613   0.01950  -0.1096   0.0205   1.0000
  12.000   1.6805   0.02757   0.02095  -0.1075   0.0160   1.0000
  12.250   1.6874   0.02900   0.02241  -0.1056   0.0130   1.0000
  12.500   1.6940   0.03051   0.02395  -0.1038   0.0108   1.0000
  12.750   1.7006   0.03207   0.02556  -0.1022   0.0089   1.0000
  13.000   1.7069   0.03370   0.02725  -0.1006   0.0075   1.0000
  13.250   1.7121   0.03549   0.02909  -0.0991   0.0063   1.0000
  13.500   1.7181   0.03727   0.03093  -0.0978   0.0054   1.0000
  13.750   1.7226   0.03927   0.03299  -0.0965   0.0047   1.0000
  14.000   1.7281   0.04122   0.03501  -0.0954   0.0041   1.0000
  14.250   1.7315   0.04344   0.03730  -0.0944   0.0034   1.0000
  14.500   1.7348   0.04576   0.03969  -0.0935   0.0028   1.0000
  14.750   1.7370   0.04828   0.04230  -0.0927   0.0023   1.0000
  15.000   1.7386   0.05095   0.04504  -0.0920   0.0018   1.0000
  15.250   1.7391   0.05383   0.04801  -0.0914   0.0014   1.0000
  15.500   1.7390   0.05688   0.05115  -0.0911   0.0012   1.0000
  15.750   1.7386   0.06007   0.05442  -0.0908   0.0010   1.0000
  16.000   1.7378   0.06341   0.05786  -0.0908   0.0009   1.0000
  16.250   1.7350   0.06711   0.06166  -0.0909   0.0007   1.0000
  16.500   1.7312   0.07107   0.06573  -0.0912   0.0006   1.0000
  16.750   1.7284   0.07499   0.06976  -0.0917   0.0006   1.0000
  17.000   1.7249   0.07913   0.07400  -0.0923   0.0005   1.0000
  17.250   1.7204   0.08348   0.07847  -0.0932   0.0005   1.0000
  17.500   1.7151   0.08806   0.08317  -0.0942   0.0005   1.0000
  17.750   1.7092   0.09287   0.08809  -0.0955   0.0005   1.0000
  18.000   1.7020   0.09799   0.09333  -0.0970   0.0004   1.0000
  18.250   1.6942   0.10328   0.09874  -0.0988   0.0004   1.0000
  18.500   1.6863   0.10868   0.10426  -0.1007   0.0004   1.0000
  18.750   1.6771   0.11438   0.11008  -0.1029   0.0004   1.0000
  19.000   1.6682   0.12011   0.11594  -0.1053   0.0004   1.0000
  19.250   1.6586   0.12604   0.12199  -0.1079   0.0003   1.0000
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