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MH 112 Airfoil (mh112-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: MH 112 Airfoil (mh112-il)
Reynolds number: 500,000
Max Cl/Cd: 109.72 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh112-il-500000-n5.txt
Download as CSV file: xf-mh112-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 112  Airfoil                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750   0.1965   0.09912   0.09565  -0.1543   0.8480   0.0125
 -10.750  -0.0517   0.04432   0.04027  -0.1757   0.8119   0.0117
 -10.500  -0.0943   0.03587   0.03150  -0.1810   0.8022   0.0115
 -10.250  -0.1124   0.03141   0.02693  -0.1835   0.7944   0.0115
 -10.000  -0.1228   0.02734   0.02262  -0.1883   0.7864   0.0115
  -9.750  -0.1159   0.02511   0.02018  -0.1902   0.7807   0.0116
  -9.500  -0.1027   0.02353   0.01845  -0.1909   0.7754   0.0117
  -9.250  -0.0860   0.02220   0.01696  -0.1914   0.7701   0.0117
  -9.000  -0.0662   0.02112   0.01573  -0.1918   0.7653   0.0118
  -8.750  -0.0451   0.02010   0.01457  -0.1920   0.7610   0.0119
  -8.500  -0.0228   0.01919   0.01354  -0.1922   0.7564   0.0120
  -8.250   0.0006   0.01836   0.01259  -0.1924   0.7515   0.0121
  -8.000   0.0249   0.01764   0.01174  -0.1926   0.7470   0.0122
  -7.750   0.0500   0.01697   0.01095  -0.1927   0.7430   0.0123
  -7.500   0.0755   0.01634   0.01024  -0.1929   0.7385   0.0124
  -7.250   0.1014   0.01576   0.00957  -0.1930   0.7338   0.0126
  -7.000   0.1277   0.01523   0.00894  -0.1931   0.7294   0.0128
  -6.750   0.1545   0.01477   0.00836  -0.1932   0.7252   0.0129
  -6.500   0.1814   0.01430   0.00783  -0.1933   0.7209   0.0132
  -6.250   0.2086   0.01388   0.00734  -0.1935   0.7163   0.0135
  -6.000   0.2359   0.01351   0.00688  -0.1935   0.7117   0.0138
  -5.750   0.2635   0.01319   0.00646  -0.1936   0.7073   0.0141
  -5.500   0.2913   0.01279   0.00603  -0.1938   0.7032   0.0145
  -5.250   0.3191   0.01250   0.00571  -0.1940   0.6986   0.0150
  -5.000   0.3469   0.01225   0.00540  -0.1940   0.6938   0.0156
  -4.750   0.3747   0.01204   0.00511  -0.1941   0.6892   0.0164
  -4.500   0.4029   0.01181   0.00484  -0.1942   0.6850   0.0173
  -4.250   0.4309   0.01160   0.00461  -0.1943   0.6803   0.0186
  -4.000   0.4588   0.01143   0.00439  -0.1943   0.6754   0.0202
  -3.750   0.4866   0.01128   0.00419  -0.1943   0.6706   0.0225
  -3.500   0.5147   0.01111   0.00402  -0.1943   0.6660   0.0261
  -3.250   0.5427   0.01096   0.00388  -0.1944   0.6612   0.0319
  -3.000   0.5705   0.01083   0.00376  -0.1944   0.6561   0.0412
  -2.750   0.5981   0.01073   0.00365  -0.1944   0.6513   0.0521
  -2.500   0.6261   0.01060   0.00357  -0.1945   0.6463   0.0656
  -2.250   0.6537   0.01050   0.00350  -0.1945   0.6411   0.0811
  -2.000   0.6811   0.01042   0.00344  -0.1944   0.6360   0.0997
  -1.750   0.7087   0.01033   0.00341  -0.1944   0.6310   0.1233
  -1.500   0.7363   0.01025   0.00339  -0.1944   0.6255   0.1494
  -1.250   0.7634   0.01019   0.00338  -0.1943   0.6201   0.1763
  -1.000   0.7902   0.01018   0.00338  -0.1942   0.6150   0.2020
  -0.750   0.8177   0.01013   0.00340  -0.1941   0.6095   0.2292
  -0.500   0.8444   0.01012   0.00342  -0.1939   0.6037   0.2572
  -0.250   0.8704   0.01013   0.00346  -0.1936   0.5980   0.2872
   0.000   0.8972   0.01012   0.00351  -0.1934   0.5922   0.3193
   0.250   0.9229   0.01015   0.00357  -0.1931   0.5852   0.3499
   0.500   0.9478   0.01020   0.00365  -0.1925   0.5784   0.3819
   0.750   0.9735   0.01024   0.00373  -0.1921   0.5712   0.4135
   1.000   0.9978   0.01031   0.00383  -0.1915   0.5641   0.4426
   1.250   1.0227   0.01038   0.00394  -0.1909   0.5580   0.4724
   1.500   1.0474   0.01046   0.00405  -0.1903   0.5514   0.4994
   1.750   1.0705   0.01058   0.00417  -0.1894   0.5451   0.5239
   2.000   1.0943   0.01067   0.00430  -0.1886   0.5392   0.5489
   2.250   1.1170   0.01076   0.00443  -0.1877   0.5329   0.5723
   2.500   1.1379   0.01090   0.00457  -0.1863   0.5268   0.5955
   2.750   1.1606   0.01101   0.00472  -0.1854   0.5209   0.6198
   3.000   1.1823   0.01115   0.00490  -0.1842   0.5143   0.6461
   3.250   1.2025   0.01133   0.00510  -0.1828   0.5082   0.6725
   3.500   1.2248   0.01145   0.00530  -0.1818   0.5022   0.7041
   3.750   1.2448   0.01160   0.00552  -0.1804   0.4954   0.7432
   4.000   1.2627   0.01175   0.00577  -0.1785   0.4894   0.7950
   4.250   1.2760   0.01163   0.00591  -0.1755   0.4834   0.9701
   4.500   1.2958   0.01190   0.00613  -0.1742   0.4764   1.0000
   4.750   1.3157   0.01220   0.00638  -0.1729   0.4701   1.0000
   5.000   1.3363   0.01247   0.00663  -0.1717   0.4633   1.0000
   5.250   1.3540   0.01283   0.00695  -0.1701   0.4561   1.0000
   5.500   1.3738   0.01314   0.00724  -0.1689   0.4491   1.0000
   5.750   1.3914   0.01353   0.00759  -0.1673   0.4413   1.0000
   6.000   1.4092   0.01392   0.00795  -0.1658   0.4345   1.0000
   6.250   1.4267   0.01434   0.00834  -0.1643   0.4262   1.0000
   6.500   1.4423   0.01484   0.00881  -0.1625   0.4185   1.0000
   6.750   1.4596   0.01529   0.00925  -0.1611   0.4100   1.0000
   7.000   1.4735   0.01588   0.00980  -0.1591   0.4017   1.0000
   7.250   1.4896   0.01642   0.01032  -0.1576   0.3925   1.0000
   7.500   1.5028   0.01710   0.01096  -0.1556   0.3839   1.0000
   7.750   1.5177   0.01772   0.01157  -0.1540   0.3748   1.0000
   8.000   1.5300   0.01849   0.01230  -0.1521   0.3658   1.0000
   8.250   1.5431   0.01925   0.01304  -0.1503   0.3563   1.0000
   8.500   1.5550   0.02010   0.01387  -0.1485   0.3473   1.0000
   8.750   1.5664   0.02100   0.01475  -0.1466   0.3381   1.0000
   9.000   1.5784   0.02190   0.01563  -0.1449   0.3299   1.0000
   9.250   1.5886   0.02294   0.01664  -0.1430   0.3210   1.0000
   9.500   1.6006   0.02390   0.01760  -0.1414   0.3140   1.0000
   9.750   1.6114   0.02496   0.01865  -0.1398   0.3061   1.0000
  10.000   1.6216   0.02609   0.01977  -0.1381   0.2992   1.0000
  10.250   1.6329   0.02718   0.02086  -0.1366   0.2918   1.0000
  10.500   1.6410   0.02852   0.02218  -0.1349   0.2850   1.0000
  10.750   1.6536   0.02957   0.02326  -0.1336   0.2788   1.0000
  11.000   1.6620   0.03096   0.02465  -0.1321   0.2720   1.0000
  11.250   1.6722   0.03225   0.02595  -0.1307   0.2662   1.0000
  11.500   1.6823   0.03357   0.02729  -0.1295   0.2599   1.0000
  11.750   1.6897   0.03515   0.02887  -0.1280   0.2539   1.0000
  12.000   1.7001   0.03651   0.03026  -0.1269   0.2482   1.0000
  12.250   1.7089   0.03803   0.03180  -0.1257   0.2421   1.0000
  12.500   1.7150   0.03983   0.03360  -0.1244   0.2362   1.0000
  12.750   1.7252   0.04130   0.03510  -0.1234   0.2304   1.0000
  13.000   1.7307   0.04322   0.03704  -0.1222   0.2246   1.0000
  13.250   1.7388   0.04494   0.03878  -0.1212   0.2192   1.0000
  13.500   1.7454   0.04684   0.04071  -0.1202   0.2130   1.0000
  13.750   1.7495   0.04902   0.04289  -0.1191   0.2075   1.0000
  14.000   1.7572   0.05088   0.04480  -0.1183   0.2018   1.0000
  14.250   1.7616   0.05311   0.04705  -0.1175   0.1958   1.0000
  14.500   1.7661   0.05538   0.04935  -0.1167   0.1906   1.0000
  14.750   1.7718   0.05753   0.05153  -0.1160   0.1850   1.0000
  15.000   1.7724   0.06032   0.05434  -0.1152   0.1795   1.0000
  15.250   1.7789   0.06245   0.05652  -0.1147   0.1745   1.0000
  15.500   1.7811   0.06515   0.05925  -0.1141   0.1692   1.0000
  15.750   1.7832   0.06787   0.06200  -0.1136   0.1641   1.0000
  16.000   1.7860   0.07055   0.06473  -0.1132   0.1588   1.0000
  16.250   1.7862   0.07360   0.06780  -0.1129   0.1540   1.0000
  16.500   1.7888   0.07639   0.07065  -0.1127   0.1495   1.0000
  16.750   1.7904   0.07933   0.07363  -0.1125   0.1446   1.0000
  17.000   1.7887   0.08276   0.07709  -0.1124   0.1403   1.0000
  17.250   1.7917   0.08556   0.07996  -0.1124   0.1362   1.0000
  17.500   1.7914   0.08885   0.08330  -0.1125   0.1318   1.0000
  17.750   1.7895   0.09241   0.08689  -0.1126   0.1280   1.0000
  18.000   1.7915   0.09542   0.08997  -0.1129   0.1241   1.0000
  18.250   1.7896   0.09903   0.09363  -0.1132   0.1200   1.0000
  18.500   1.7883   0.10255   0.09719  -0.1136   0.1166   1.0000
  18.750   1.7883   0.10590   0.10062  -0.1141   0.1129   1.0000
  19.000   1.7865   0.10952   0.10428  -0.1147   0.1092   1.0000
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