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MH 114 13.02% (mh114-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 114 13.02% (mh114-il)
Reynolds number: 200,000
Max Cl/Cd: 89.71 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh114-il-200000.txt
Download as CSV file: xf-mh114-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 114  13.02%                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.0165   0.09932   0.09578  -0.0986   0.9441   0.0401
  -8.500  -0.0095   0.09560   0.09208  -0.1060   0.9387   0.0420
  -8.250   0.0039   0.09078   0.08727  -0.1147   0.9359   0.0424
  -8.000   0.0192   0.08791   0.08440  -0.1117   0.9310   0.0432
  -7.750   0.0372   0.08508   0.08156  -0.1129   0.9267   0.0442
  -7.500   0.0581   0.08161   0.07809  -0.1168   0.9240   0.0462
  -7.250   0.0783   0.07722   0.07369  -0.1245   0.9215   0.0491
  -7.000   0.0671   0.07308   0.06959  -0.1339   0.9076   0.0503
  -6.750   0.0906   0.06961   0.06612  -0.1321   0.9070   0.0515
  -6.500   0.1193   0.06659   0.06307  -0.1352   0.9055   0.0533
  -6.250   0.1168   0.06486   0.06136  -0.1341   0.8944   0.0547
  -6.000   0.1763   0.04094   0.03756  -0.1397   0.8746   0.0621
  -5.750   0.1435   0.05262   0.04897  -0.1558   0.8777   0.0610
  -5.500   0.1715   0.05064   0.04700  -0.1566   0.8756   0.0628
  -5.250   0.1813   0.04816   0.04447  -0.1577   0.8672   0.0654
  -5.000   0.2249   0.02685   0.02081  -0.1783   0.8606   0.0298
  -4.750   0.2629   0.02521   0.01922  -0.1813   0.8587   0.0330
  -4.500   0.2832   0.02370   0.01730  -0.1804   0.8510   0.0342
  -4.250   0.3186   0.02172   0.01487  -0.1820   0.8471   0.0347
  -4.000   0.3573   0.01986   0.01276  -0.1840   0.8444   0.0367
  -3.750   0.3966   0.01882   0.01157  -0.1860   0.8421   0.0415
  -3.500   0.4146   0.01835   0.01116  -0.1844   0.8338   0.0469
  -3.250   0.4496   0.01742   0.01018  -0.1857   0.8298   0.0576
  -3.000   0.4879   0.01647   0.00926  -0.1877   0.8268   0.0773
  -2.750   0.5125   0.01606   0.00894  -0.1872   0.8200   0.1040
  -2.500   0.5448   0.01546   0.00848  -0.1882   0.8148   0.1575
  -2.250   0.5816   0.01484   0.00809  -0.1901   0.8112   0.2385
  -2.000   0.6076   0.01466   0.00809  -0.1900   0.8046   0.3083
  -1.750   0.6374   0.01441   0.00798  -0.1903   0.7988   0.3807
  -1.500   0.6723   0.01409   0.00777  -0.1915   0.7948   0.4554
  -1.250   0.6958   0.01407   0.00790  -0.1907   0.7875   0.5143
  -1.000   0.7252   0.01392   0.00782  -0.1907   0.7817   0.5739
  -0.750   0.7589   0.01369   0.00763  -0.1914   0.7776   0.6305
  -0.500   0.7782   0.01376   0.00782  -0.1896   0.7692   0.6774
  -0.250   0.8068   0.01358   0.00769  -0.1892   0.7639   0.7284
   0.000   0.8289   0.01353   0.00772  -0.1877   0.7573   0.7780
   0.250   0.8479   0.01339   0.00767  -0.1854   0.7503   0.8327
   0.500   0.8689   0.01307   0.00734  -0.1831   0.7455   0.9137
   0.750   0.8943   0.01310   0.00736  -0.1827   0.7367   1.0000
   1.000   0.9292   0.01308   0.00716  -0.1841   0.7310   1.0000
   1.250   0.9551   0.01323   0.00725  -0.1839   0.7228   1.0000
   1.500   0.9864   0.01325   0.00714  -0.1845   0.7162   1.0000
   1.750   1.0134   0.01337   0.00719  -0.1844   0.7084   1.0000
   2.000   1.0425   0.01343   0.00715  -0.1846   0.7009   1.0000
   2.250   1.0698   0.01354   0.00720  -0.1845   0.6931   1.0000
   2.500   1.0976   0.01362   0.00721  -0.1845   0.6850   1.0000
   2.750   1.1242   0.01374   0.00728  -0.1842   0.6769   1.0000
   3.000   1.1518   0.01383   0.00730  -0.1841   0.6686   1.0000
   3.250   1.1770   0.01398   0.00742  -0.1836   0.6596   1.0000
   3.500   1.2053   0.01407   0.00743  -0.1837   0.6514   1.0000
   3.750   1.2285   0.01425   0.00761  -0.1828   0.6416   1.0000
   4.000   1.2577   0.01436   0.00761  -0.1831   0.6334   1.0000
   4.250   1.2793   0.01456   0.00783  -0.1819   0.6228   1.0000
   4.500   1.3043   0.01474   0.00799  -0.1814   0.6133   1.0000
   4.750   1.3300   0.01491   0.00809  -0.1810   0.6037   1.0000
   5.000   1.3515   0.01515   0.00834  -0.1798   0.5928   1.0000
   5.250   1.3762   0.01537   0.00852  -0.1793   0.5829   1.0000
   5.500   1.3994   0.01560   0.00872  -0.1785   0.5723   1.0000
   5.750   1.4199   0.01588   0.00902  -0.1772   0.5611   1.0000
   6.000   1.4427   0.01616   0.00926  -0.1763   0.5505   1.0000
   6.250   1.4651   0.01645   0.00950  -0.1754   0.5396   1.0000
   6.500   1.4832   0.01678   0.00987  -0.1736   0.5280   1.0000
   6.750   1.5034   0.01712   0.01020  -0.1724   0.5169   1.0000
   7.000   1.5251   0.01748   0.01049  -0.1713   0.5062   1.0000
   7.250   1.5408   0.01786   0.01091  -0.1692   0.4944   1.0000
   7.500   1.5573   0.01827   0.01133  -0.1673   0.4832   1.0000
   7.750   1.5747   0.01869   0.01172  -0.1656   0.4724   1.0000
   8.000   1.5889   0.01913   0.01217  -0.1632   0.4613   1.0000
   8.250   1.6015   0.01962   0.01270  -0.1607   0.4502   1.0000
   8.500   1.6165   0.02014   0.01321  -0.1587   0.4395   1.0000
   8.750   1.6300   0.02069   0.01374  -0.1564   0.4287   1.0000
   9.000   1.6405   0.02129   0.01441  -0.1537   0.4176   1.0000
   9.250   1.6531   0.02193   0.01505  -0.1514   0.4071   1.0000
   9.500   1.6652   0.02261   0.01571  -0.1491   0.3965   1.0000
   9.750   1.6737   0.02336   0.01655  -0.1463   0.3855   1.0000
  10.000   1.6838   0.02416   0.01737  -0.1439   0.3749   1.0000
  10.250   1.6943   0.02501   0.01818  -0.1416   0.3646   1.0000
  10.500   1.7008   0.02596   0.01923  -0.1389   0.3535   1.0000
  10.750   1.7089   0.02696   0.02028  -0.1364   0.3431   1.0000
  11.000   1.7170   0.02803   0.02131  -0.1341   0.3327   1.0000
  11.250   1.7220   0.02922   0.02261  -0.1315   0.3218   1.0000
  11.500   1.7278   0.03048   0.02392  -0.1292   0.3112   1.0000
  11.750   1.7333   0.03183   0.02525  -0.1269   0.3010   1.0000
  12.000   1.7369   0.03331   0.02682  -0.1246   0.2901   1.0000
  12.250   1.7407   0.03487   0.02845  -0.1224   0.2793   1.0000
  12.500   1.7437   0.03657   0.03015  -0.1203   0.2691   1.0000
  12.750   1.7456   0.03839   0.03201  -0.1182   0.2586   1.0000
  13.000   1.7476   0.04031   0.03402  -0.1163   0.2480   1.0000
  13.250   1.7488   0.04239   0.03612  -0.1145   0.2380   1.0000
  13.500   1.7487   0.04464   0.03840  -0.1127   0.2280   1.0000
  13.750   1.7492   0.04696   0.04082  -0.1112   0.2175   1.0000
  14.000   1.7487   0.04946   0.04336  -0.1097   0.2079   1.0000
  14.250   1.7466   0.05220   0.04608  -0.1084   0.1986   1.0000
  14.500   1.7460   0.05492   0.04893  -0.1073   0.1888   1.0000
  14.750   1.7439   0.05788   0.05192  -0.1062   0.1799   1.0000
  15.000   1.7404   0.06107   0.05513  -0.1053   0.1713   1.0000
  15.250   1.7383   0.06425   0.05844  -0.1047   0.1624   1.0000
  15.500   1.7338   0.06776   0.06194  -0.1040   0.1546   1.0000
  15.750   1.7301   0.07130   0.06559  -0.1037   0.1463   1.0000
  16.000   1.7257   0.07501   0.06936  -0.1034   0.1388   1.0000
  16.250   1.7201   0.07897   0.07336  -0.1034   0.1316   1.0000
  16.500   1.7159   0.08287   0.07737  -0.1035   0.1245   1.0000
  16.750   1.7091   0.08713   0.08164  -0.1038   0.1181   1.0000
  17.000   1.7046   0.09122   0.08587  -0.1042   0.1116   1.0000
  17.250   1.6974   0.09569   0.09034  -0.1048   0.1058   1.0000
  17.500   1.6925   0.09997   0.09476  -0.1055   0.0998   1.0000
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