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MH 115 11.06% (mh115-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: MH 115 11.06% (mh115-il)
Reynolds number: 500,000
Max Cl/Cd: 120.36 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh115-il-500000-n5.txt
Download as CSV file: xf-mh115-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.0447   0.08205   0.07972  -0.0867   0.9490   0.0075
  -9.500  -0.0316   0.07810   0.07577  -0.0899   0.9462   0.0073
  -9.250  -0.1266   0.09077   0.08836  -0.0810   0.9612   0.0075
  -9.000  -0.1153   0.08773   0.08533  -0.0833   0.9554   0.0073
  -8.750  -0.1025   0.08403   0.08163  -0.0867   0.9498   0.0071
  -8.500  -0.0869   0.07964   0.07723  -0.0916   0.9455   0.0068
  -8.250  -0.0730   0.07463   0.07221  -0.0970   0.9381   0.0064
  -8.000  -0.0647   0.06361   0.06116  -0.1091   0.9293   0.0055
  -7.750  -0.0550   0.05643   0.05394  -0.1188   0.9145   0.0054
  -7.500  -0.0947   0.02167   0.01778  -0.1575   0.8769   0.0048
  -7.250  -0.0715   0.01872   0.01430  -0.1592   0.8680   0.0048
  -7.000  -0.0461   0.01695   0.01216  -0.1600   0.8594   0.0048
  -6.750  -0.0199   0.01559   0.01049  -0.1605   0.8512   0.0049
  -6.500   0.0071   0.01455   0.00920  -0.1609   0.8431   0.0050
  -6.250   0.0341   0.01368   0.00812  -0.1611   0.8350   0.0051
  -6.000   0.0617   0.01298   0.00723  -0.1613   0.8271   0.0052
  -5.750   0.0892   0.01238   0.00649  -0.1614   0.8190   0.0053
  -5.500   0.1170   0.01183   0.00576  -0.1616   0.8112   0.0056
  -5.250   0.1447   0.01132   0.00515  -0.1617   0.8032   0.0060
  -4.750   0.2005   0.01064   0.00425  -0.1619   0.7876   0.0072
  -4.250   0.2565   0.01006   0.00350  -0.1620   0.7723   0.0106
  -3.750   0.3124   0.00964   0.00303  -0.1621   0.7572   0.0221
  -3.250   0.3682   0.00931   0.00268  -0.1622   0.7422   0.0411
  -3.000   0.3961   0.00917   0.00252  -0.1622   0.7347   0.0541
  -2.750   0.4241   0.00903   0.00239  -0.1622   0.7270   0.0696
  -2.500   0.4519   0.00892   0.00228  -0.1622   0.7194   0.0887
  -2.250   0.4799   0.00881   0.00218  -0.1623   0.7116   0.1099
  -2.000   0.5076   0.00872   0.00211  -0.1623   0.7040   0.1360
  -1.750   0.5356   0.00861   0.00205  -0.1623   0.6962   0.1666
  -1.250   0.5911   0.00843   0.00199  -0.1624   0.6805   0.2447
  -0.750   0.6465   0.00831   0.00198  -0.1624   0.6646   0.3246
  -0.500   0.6739   0.00828   0.00200  -0.1624   0.6567   0.3681
  -0.250   0.7017   0.00822   0.00203  -0.1624   0.6482   0.4153
   0.000   0.7290   0.00820   0.00207  -0.1624   0.6401   0.4639
   0.250   0.7564   0.00816   0.00213  -0.1623   0.6313   0.5131
   0.500   0.7835   0.00815   0.00219  -0.1622   0.6228   0.5626
   0.750   0.8104   0.00815   0.00227  -0.1620   0.6136   0.6124
   1.000   0.8372   0.00814   0.00235  -0.1618   0.6046   0.6617
   1.250   0.8631   0.00816   0.00245  -0.1613   0.5953   0.7125
   1.500   0.8887   0.00815   0.00255  -0.1608   0.5852   0.7650
   1.750   0.9125   0.00815   0.00265  -0.1598   0.5757   0.8234
   2.250   0.9567   0.00811   0.00273  -0.1570   0.5549   1.0000
   2.500   0.9830   0.00827   0.00282  -0.1568   0.5438   1.0000
   2.750   1.0089   0.00845   0.00294  -0.1564   0.5320   1.0000
   3.250   1.0603   0.00882   0.00318  -0.1557   0.5069   1.0000
   3.500   1.0856   0.00902   0.00332  -0.1553   0.4936   1.0000
   3.750   1.1105   0.00923   0.00349  -0.1548   0.4798   1.0000
   4.000   1.1352   0.00947   0.00366  -0.1542   0.4656   1.0000
   4.250   1.1595   0.00972   0.00385  -0.1536   0.4508   1.0000
   4.500   1.1834   0.00998   0.00406  -0.1530   0.4356   1.0000
   4.750   1.2070   0.01026   0.00427  -0.1523   0.4204   1.0000
   5.000   1.2301   0.01057   0.00451  -0.1515   0.4041   1.0000
   5.250   1.2529   0.01088   0.00477  -0.1506   0.3882   1.0000
   5.500   1.2752   0.01122   0.00504  -0.1497   0.3717   1.0000
   5.750   1.2970   0.01158   0.00534  -0.1487   0.3549   1.0000
   6.000   1.3182   0.01196   0.00565  -0.1476   0.3383   1.0000
   6.250   1.3389   0.01236   0.00599  -0.1465   0.3218   1.0000
   6.500   1.3595   0.01276   0.00633  -0.1453   0.3057   1.0000
   6.750   1.3795   0.01316   0.00668  -0.1440   0.2912   1.0000
   7.000   1.3981   0.01357   0.00705  -0.1425   0.2769   1.0000
   7.250   1.4161   0.01399   0.00744  -0.1408   0.2627   1.0000
   7.500   1.4339   0.01442   0.00784  -0.1392   0.2496   1.0000
   7.750   1.4511   0.01489   0.00828  -0.1375   0.2359   1.0000
   8.000   1.4677   0.01539   0.00875  -0.1357   0.2230   1.0000
   8.250   1.4842   0.01589   0.00923  -0.1339   0.2115   1.0000
   8.500   1.4998   0.01645   0.00977  -0.1320   0.1991   1.0000
   8.750   1.5146   0.01705   0.01034  -0.1301   0.1868   1.0000
   9.250   1.5431   0.01835   0.01161  -0.1261   0.1636   1.0000
   9.500   1.5563   0.01906   0.01232  -0.1241   0.1521   1.0000
   9.750   1.5690   0.01984   0.01308  -0.1221   0.1413   1.0000
  10.000   1.5798   0.02074   0.01394  -0.1199   0.1286   1.0000
  10.250   1.5891   0.02176   0.01493  -0.1175   0.1148   1.0000
  10.500   1.5978   0.02286   0.01598  -0.1153   0.1021   1.0000
  10.750   1.6067   0.02398   0.01708  -0.1131   0.0922   1.0000
  11.000   1.6155   0.02515   0.01825  -0.1111   0.0838   1.0000
  11.250   1.6256   0.02625   0.01938  -0.1093   0.0772   1.0000
  11.500   1.6336   0.02756   0.02070  -0.1073   0.0706   1.0000
  11.750   1.6423   0.02885   0.02203  -0.1056   0.0643   1.0000
  12.000   1.6491   0.03033   0.02353  -0.1038   0.0580   1.0000
  12.250   1.6541   0.03201   0.02521  -0.1019   0.0510   1.0000
  12.500   1.6593   0.03375   0.02696  -0.1003   0.0440   1.0000
  12.750   1.6620   0.03576   0.02898  -0.0986   0.0364   1.0000
  13.000   1.6622   0.03809   0.03129  -0.0969   0.0286   1.0000
  13.250   1.6617   0.04058   0.03379  -0.0954   0.0221   1.0000
  13.500   1.6619   0.04311   0.03635  -0.0941   0.0175   1.0000
  13.750   1.6622   0.04572   0.03901  -0.0930   0.0143   1.0000
  14.000   1.6640   0.04827   0.04164  -0.0921   0.0122   1.0000
  14.250   1.6649   0.05100   0.04445  -0.0914   0.0106   1.0000
  14.500   1.6657   0.05384   0.04738  -0.0908   0.0091   1.0000
  14.750   1.6658   0.05684   0.05047  -0.0903   0.0081   1.0000
  15.000   1.6658   0.05997   0.05370  -0.0901   0.0071   1.0000
  15.250   1.6641   0.06341   0.05723  -0.0899   0.0064   1.0000
  15.500   1.6634   0.06680   0.06074  -0.0900   0.0057   1.0000
  15.750   1.6608   0.07056   0.06461  -0.0902   0.0050   1.0000
  16.000   1.6572   0.07456   0.06873  -0.0906   0.0046   1.0000
  16.250   1.6544   0.07858   0.07286  -0.0912   0.0041   1.0000
  16.500   1.6498   0.08293   0.07734  -0.0920   0.0036   1.0000
  16.750   1.6435   0.08766   0.08219  -0.0931   0.0032   1.0000
  17.000   1.6386   0.09229   0.08695  -0.0942   0.0029   1.0000
  17.250   1.6323   0.09724   0.09203  -0.0956   0.0026   1.0000
  17.500   1.6247   0.10250   0.09741  -0.0973   0.0024   1.0000
  17.750   1.6162   0.10802   0.10307  -0.0993   0.0022   1.0000
  18.000   1.6075   0.11366   0.10884  -0.1014   0.0020   1.0000
  18.250   1.5997   0.11923   0.11454  -0.1037   0.0019   1.0000
  18.500   1.5914   0.12494   0.12039  -0.1062   0.0018   1.0000
  18.750   1.5821   0.13089   0.12648  -0.1089   0.0016   1.0000
  19.000   1.5731   0.13686   0.13258  -0.1119   0.0015   1.0000
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