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MH 115 11.06% (mh115-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 115 11.06% (mh115-il)
Reynolds number: 100,000
Max Cl/Cd: 61.9 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh115-il-100000.txt
Download as CSV file: xf-mh115-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3407   0.12414   0.11993  -0.0292   1.0000   0.0676
  -8.250  -0.3583   0.12390   0.11978  -0.0280   1.0000   0.0677
  -8.000  -0.3753   0.12343   0.11941  -0.0265   1.0000   0.0678
  -7.750  -0.3398   0.11519   0.11113  -0.0227   1.0000   0.0702
  -7.500  -0.3435   0.11351   0.10950  -0.0207   1.0000   0.0714
  -7.250  -0.3338   0.11062   0.10663  -0.0226   0.9969   0.0738
  -7.000  -0.3198   0.10730   0.10331  -0.0276   0.9909   0.0770
  -6.750  -0.3230   0.10575   0.10181  -0.0352   0.9812   0.0799
  -6.500  -0.3117   0.10154   0.09764  -0.0493   0.9706   0.0810
  -6.250  -0.2929   0.09718   0.09327  -0.0410   0.9687   0.0834
  -6.000  -0.2745   0.09390   0.08998  -0.0431   0.9623   0.0872
  -5.750  -0.2626   0.09047   0.08655  -0.0509   0.9524   0.0927
  -5.500  -0.2404   0.08520   0.08128  -0.0585   0.9463   0.0972
  -5.250  -0.2305   0.08293   0.07903  -0.0572   0.9380   0.1016
  -5.000  -0.1982   0.07637   0.07235  -0.0754   0.9291   0.1104
  -4.750  -0.1899   0.07462   0.07067  -0.0696   0.9225   0.1142
  -4.500  -0.1472   0.06839   0.06428  -0.0837   0.9174   0.1266
  -4.250  -0.1394   0.06644   0.06235  -0.0814   0.9085   0.1300
  -4.000  -0.0969   0.06112   0.05688  -0.0916   0.9037   0.1434
  -3.750  -0.0177   0.04820   0.04317  -0.1127   0.9020   0.1001
  -3.500   0.0583   0.03575   0.02891  -0.1262   0.9007   0.0614
  -3.250   0.0924   0.03352   0.02602  -0.1280   0.8937   0.0659
  -3.000   0.1375   0.03119   0.02331  -0.1314   0.8900   0.0746
  -2.750   0.1865   0.02946   0.02120  -0.1349   0.8872   0.0922
  -2.500   0.2088   0.02882   0.02044  -0.1342   0.8782   0.1077
  -2.250   0.2516   0.02763   0.01927  -0.1368   0.8742   0.1365
  -2.000   0.2846   0.02690   0.01867  -0.1379   0.8680   0.1755
  -1.750   0.3177   0.02628   0.01830  -0.1391   0.8614   0.2394
  -1.500   0.3623   0.02535   0.01782  -0.1420   0.8578   0.3553
  -1.250   0.3837   0.02526   0.01809  -0.1412   0.8488   0.4589
  -1.000   0.4206   0.02463   0.01791  -0.1420   0.8441   0.6061
  -0.750   0.4404   0.02441   0.01805  -0.1396   0.8369   0.7365
  -0.500   0.4581   0.02378   0.01769  -0.1362   0.8295   1.0000
  -0.250   0.5105   0.02342   0.01695  -0.1404   0.8267   1.0000
   0.000   0.5296   0.02400   0.01734  -0.1394   0.8157   1.0000
   0.250   0.5787   0.02356   0.01666  -0.1427   0.8126   1.0000
   0.500   0.6000   0.02405   0.01700  -0.1419   0.8024   1.0000
   0.750   0.6464   0.02365   0.01643  -0.1446   0.7984   1.0000
   1.000   0.6902   0.02328   0.01591  -0.1469   0.7943   1.0000
   1.250   0.7134   0.02362   0.01617  -0.1462   0.7842   1.0000
   1.500   0.7614   0.02299   0.01542  -0.1489   0.7810   1.0000
   1.750   0.7806   0.02348   0.01586  -0.1475   0.7698   1.0000
   2.000   0.8271   0.02283   0.01512  -0.1499   0.7660   1.0000
   2.250   0.8479   0.02324   0.01551  -0.1488   0.7550   1.0000
   2.500   0.8934   0.02258   0.01477  -0.1510   0.7506   1.0000
   2.750   0.9146   0.02295   0.01513  -0.1498   0.7393   1.0000
   3.000   0.9604   0.02224   0.01436  -0.1519   0.7346   1.0000
   3.250   0.9811   0.02260   0.01475  -0.1506   0.7228   1.0000
   3.500   1.0111   0.02257   0.01470  -0.1506   0.7135   1.0000
   3.750   1.0480   0.02220   0.01429  -0.1515   0.7054   1.0000
   4.000   1.0720   0.02240   0.01454  -0.1506   0.6939   1.0000
   4.250   1.1053   0.02220   0.01432  -0.1510   0.6846   1.0000
   4.500   1.1379   0.02201   0.01412  -0.1512   0.6744   1.0000
   4.750   1.1618   0.02218   0.01434  -0.1503   0.6619   1.0000
   5.000   1.1890   0.02222   0.01440  -0.1497   0.6500   1.0000
   5.250   1.2201   0.02210   0.01428  -0.1498   0.6387   1.0000
   5.500   1.2523   0.02194   0.01411  -0.1500   0.6269   1.0000
   5.750   1.2761   0.02209   0.01430  -0.1489   0.6129   1.0000
   6.000   1.3005   0.02222   0.01446  -0.1480   0.5987   1.0000
   6.250   1.3251   0.02235   0.01464  -0.1471   0.5841   1.0000
   6.500   1.3496   0.02249   0.01480  -0.1462   0.5690   1.0000
   6.750   1.3739   0.02264   0.01497  -0.1452   0.5534   1.0000
   7.000   1.3978   0.02282   0.01514  -0.1442   0.5373   1.0000
   7.250   1.4214   0.02302   0.01536  -0.1431   0.5207   1.0000
   7.500   1.4429   0.02331   0.01564  -0.1418   0.5033   1.0000
   7.750   1.4604   0.02373   0.01612  -0.1398   0.4849   1.0000
   8.000   1.4785   0.02416   0.01659  -0.1380   0.4664   1.0000
   8.250   1.4968   0.02461   0.01704  -0.1362   0.4479   1.0000
   8.500   1.5153   0.02511   0.01750  -0.1345   0.4295   1.0000
   8.750   1.5311   0.02573   0.01812  -0.1324   0.4111   1.0000
   9.000   1.5438   0.02645   0.01890  -0.1299   0.3923   1.0000
   9.250   1.5564   0.02720   0.01966  -0.1275   0.3739   1.0000
   9.500   1.5685   0.02800   0.02046  -0.1250   0.3560   1.0000
   9.750   1.5795   0.02886   0.02129  -0.1224   0.3385   1.0000
  10.000   1.5888   0.02980   0.02217  -0.1196   0.3215   1.0000
  10.250   1.5938   0.03083   0.02327  -0.1161   0.3051   1.0000
  10.500   1.5981   0.03196   0.02443  -0.1128   0.2890   1.0000
  10.750   1.6022   0.03319   0.02568  -0.1096   0.2733   1.0000
  11.000   1.6057   0.03452   0.02704  -0.1065   0.2581   1.0000
  11.250   1.6089   0.03596   0.02850  -0.1036   0.2434   1.0000
  11.500   1.6121   0.03751   0.03006  -0.1008   0.2294   1.0000
  11.750   1.6151   0.03915   0.03170  -0.0982   0.2159   1.0000
  12.000   1.6185   0.04087   0.03340  -0.0958   0.2030   1.0000
  12.250   1.6171   0.04279   0.03545  -0.0931   0.1913   1.0000
  12.500   1.6158   0.04487   0.03764  -0.0907   0.1800   1.0000
  12.750   1.6154   0.04703   0.03987  -0.0885   0.1694   1.0000
  13.000   1.6158   0.04920   0.04204  -0.0867   0.1591   1.0000
  13.250   1.6124   0.05163   0.04456  -0.0848   0.1495   1.0000
  13.500   1.6078   0.05439   0.04748  -0.0831   0.1404   1.0000
  13.750   1.6055   0.05706   0.05016  -0.0817   0.1314   1.0000
  14.000   1.5992   0.06007   0.05329  -0.0804   0.1230   1.0000
  14.250   1.5921   0.06347   0.05686  -0.0794   0.1148   1.0000
  14.500   1.5881   0.06663   0.05998  -0.0786   0.1064   1.0000
  14.750   1.5775   0.07063   0.06420  -0.0781   0.0991   1.0000
  15.000   1.5699   0.07459   0.06825  -0.0778   0.0915   1.0000
  15.250   1.5669   0.07807   0.07158  -0.0775   0.0830   1.0000
  15.500   1.5519   0.08330   0.07719  -0.0780   0.0777   1.0000
  15.750   1.5480   0.08714   0.08094  -0.0781   0.0707   1.0000
  16.000   1.5349   0.09253   0.08664  -0.0791   0.0660   1.0000
  16.250   1.5330   0.09627   0.09027  -0.0794   0.0600   1.0000
  16.500   1.5190   0.10211   0.09646  -0.0811   0.0567   1.0000
  16.750   1.5174   0.10582   0.10009  -0.0820   0.0520   1.0000
  17.000   1.5074   0.11136   0.10588  -0.0836   0.0492   1.0000
  17.250   1.4944   0.11747   0.11227  -0.0862   0.0469   1.0000
  17.500   1.4917   0.12157   0.11637  -0.0878   0.0436   1.0000
  17.750   1.4855   0.12670   0.12162  -0.0897   0.0414   1.0000
  18.000   1.4693   0.13389   0.12913  -0.0936   0.0404   1.0000
  18.250   1.4538   0.14123   0.13674  -0.0979   0.0395   1.0000
  18.500   1.4371   0.14911   0.14488  -0.1027   0.0391   1.0000
  18.750   1.4168   0.15818   0.15421  -0.1087   0.0392   1.0000
  19.000   1.3929   0.16869   0.16495  -0.1160   0.0402   1.0000
  19.250   1.3689   0.17984   0.17627  -0.1238   0.0413   1.0000
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