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MH 114 13.02% (mh114-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 114 13.02% (mh114-il)
Reynolds number: 200,000
Max Cl/Cd: 88.62 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh114-il-200000-n5.txt
Download as CSV file: xf-mh114-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.0506   0.11509   0.11125  -0.0931   0.9513   0.0244
 -10.500  -0.0400   0.11146   0.10762  -0.0968   0.9479   0.0246
 -10.250  -0.0329   0.10803   0.10421  -0.0995   0.9418   0.0247
 -10.000  -0.0211   0.10417   0.10034  -0.1034   0.9383   0.0248
  -9.750  -0.0061   0.10003   0.09619  -0.1077   0.9358   0.0248
  -9.500   0.0042   0.09639   0.09256  -0.1104   0.9297   0.0248
  -9.250   0.0200   0.09278   0.08893  -0.1138   0.9255   0.0248
  -8.750   0.0582   0.08431   0.08041  -0.1199   0.9200   0.0160
  -8.250   0.0781   0.07432   0.07038  -0.1288   0.9069   0.0137
  -8.000   0.0899   0.07108   0.06713  -0.1317   0.8994   0.0134
  -7.750   0.1029   0.06738   0.06341  -0.1355   0.8924   0.0132
  -7.500   0.1073   0.06346   0.05949  -0.1383   0.8834   0.0131
  -7.250   0.1118   0.05946   0.05547  -0.1415   0.8749   0.0130
  -7.000   0.1069   0.05532   0.05134  -0.1439   0.8641   0.0129
  -6.750   0.1077   0.04803   0.04401  -0.1527   0.8547   0.0126
  -6.500   0.1010   0.02815   0.02299  -0.1748   0.8424   0.0119
  -6.250   0.1216   0.02479   0.01908  -0.1768   0.8356   0.0123
  -6.000   0.1485   0.02231   0.01609  -0.1786   0.8302   0.0127
  -5.750   0.1803   0.02033   0.01355  -0.1804   0.8263   0.0139
  -5.500   0.2051   0.01971   0.01288  -0.1805   0.8204   0.0148
  -5.250   0.2330   0.01883   0.01179  -0.1809   0.8150   0.0161
  -5.000   0.2642   0.01770   0.01037  -0.1818   0.8109   0.0171
  -4.750   0.2911   0.01699   0.00959  -0.1820   0.8053   0.0180
  -4.500   0.3188   0.01634   0.00883  -0.1822   0.7997   0.0195
  -4.250   0.3497   0.01569   0.00806  -0.1830   0.7953   0.0215
  -4.000   0.3778   0.01529   0.00757  -0.1832   0.7899   0.0253
  -3.750   0.4056   0.01488   0.00710  -0.1834   0.7840   0.0294
  -3.500   0.4364   0.01445   0.00661  -0.1841   0.7793   0.0361
  -3.250   0.4649   0.01409   0.00623  -0.1844   0.7738   0.0460
  -3.000   0.4928   0.01380   0.00593  -0.1845   0.7678   0.0606
  -2.750   0.5235   0.01349   0.00562  -0.1852   0.7629   0.0833
  -2.500   0.5513   0.01323   0.00546  -0.1853   0.7569   0.1150
  -2.250   0.5794   0.01301   0.00532  -0.1855   0.7508   0.1551
  -2.000   0.6101   0.01279   0.00515  -0.1862   0.7459   0.2008
  -1.750   0.6365   0.01266   0.00512  -0.1861   0.7391   0.2482
  -1.500   0.6651   0.01251   0.00506  -0.1863   0.7331   0.3014
  -1.250   0.6940   0.01239   0.00502  -0.1866   0.7274   0.3553
  -1.000   0.7205   0.01232   0.00505  -0.1864   0.7203   0.4060
  -0.750   0.7495   0.01224   0.00501  -0.1866   0.7145   0.4563
  -0.500   0.7756   0.01221   0.00507  -0.1863   0.7074   0.5032
  -0.250   0.8028   0.01217   0.00509  -0.1861   0.7008   0.5489
   0.000   0.8293   0.01216   0.00513  -0.1857   0.6942   0.5927
   0.250   0.8547   0.01216   0.00520  -0.1851   0.6867   0.6348
   0.500   0.8812   0.01216   0.00522  -0.1847   0.6803   0.6769
   0.750   0.9047   0.01216   0.00531  -0.1837   0.6723   0.7187
   1.250   0.9493   0.01214   0.00541  -0.1810   0.6573   0.8142
   1.500   0.9677   0.01206   0.00536  -0.1787   0.6503   0.8863
   1.750   0.9918   0.01204   0.00535  -0.1778   0.6416   1.0000
   2.250   1.0448   0.01235   0.00550  -0.1775   0.6249   1.0000
   2.500   1.0713   0.01252   0.00557  -0.1773   0.6166   1.0000
   2.750   1.0963   0.01270   0.00570  -0.1768   0.6073   1.0000
   3.000   1.1218   0.01289   0.00582  -0.1764   0.5985   1.0000
   3.250   1.1466   0.01309   0.00596  -0.1759   0.5892   1.0000
   3.500   1.1708   0.01330   0.00613  -0.1753   0.5797   1.0000
   4.000   1.2184   0.01376   0.00649  -0.1740   0.5602   1.0000
   4.250   1.2416   0.01401   0.00668  -0.1732   0.5506   1.0000
   4.500   1.2643   0.01427   0.00691  -0.1723   0.5404   1.0000
   4.750   1.2862   0.01454   0.00716  -0.1713   0.5301   1.0000
   5.000   1.3079   0.01484   0.00740  -0.1703   0.5202   1.0000
   5.250   1.3286   0.01514   0.00768  -0.1691   0.5095   1.0000
   5.500   1.3485   0.01545   0.00798  -0.1677   0.4992   1.0000
   5.750   1.3673   0.01579   0.00828  -0.1662   0.4890   1.0000
   6.000   1.3856   0.01615   0.00862  -0.1646   0.4783   1.0000
   6.250   1.4036   0.01653   0.00900  -0.1629   0.4678   1.0000
   6.500   1.4208   0.01695   0.00938  -0.1612   0.4576   1.0000
   6.750   1.4377   0.01737   0.00981  -0.1594   0.4467   1.0000
   7.000   1.4543   0.01782   0.01026  -0.1576   0.4364   1.0000
   7.250   1.4698   0.01833   0.01075  -0.1557   0.4261   1.0000
   7.500   1.4854   0.01884   0.01127  -0.1539   0.4154   1.0000
   7.750   1.5005   0.01939   0.01182  -0.1520   0.4052   1.0000
   8.000   1.5143   0.02001   0.01243  -0.1499   0.3953   1.0000
   8.250   1.5288   0.02061   0.01306  -0.1481   0.3847   1.0000
   8.500   1.5423   0.02128   0.01374  -0.1461   0.3749   1.0000
   8.750   1.5544   0.02203   0.01449  -0.1440   0.3648   1.0000
   9.000   1.5678   0.02275   0.01526  -0.1421   0.3545   1.0000
   9.250   1.5795   0.02358   0.01610  -0.1401   0.3448   1.0000
   9.500   1.5906   0.02447   0.01701  -0.1381   0.3348   1.0000
   9.750   1.6020   0.02537   0.01795  -0.1361   0.3245   1.0000
  10.000   1.6118   0.02639   0.01900  -0.1341   0.3149   1.0000
  10.250   1.6215   0.02746   0.02009  -0.1321   0.3047   1.0000
  10.500   1.6315   0.02854   0.02123  -0.1303   0.2948   1.0000
  10.750   1.6391   0.02981   0.02251  -0.1283   0.2852   1.0000
  11.000   1.6477   0.03107   0.02381  -0.1264   0.2750   1.0000
  11.250   1.6556   0.03241   0.02521  -0.1246   0.2652   1.0000
  11.500   1.6611   0.03395   0.02677  -0.1227   0.2555   1.0000
  11.750   1.6680   0.03546   0.02834  -0.1210   0.2453   1.0000
  12.000   1.6740   0.03710   0.03002  -0.1194   0.2356   1.0000
  12.250   1.6777   0.03896   0.03191  -0.1176   0.2262   1.0000
  12.500   1.6830   0.04077   0.03378  -0.1161   0.2161   1.0000
  12.750   1.6870   0.04275   0.03581  -0.1146   0.2066   1.0000
  13.000   1.6885   0.04502   0.03810  -0.1132   0.1976   1.0000
  13.250   1.6925   0.04714   0.04029  -0.1119   0.1880   1.0000
  13.500   1.6946   0.04949   0.04270  -0.1107   0.1794   1.0000
  13.750   1.6949   0.05212   0.04536  -0.1096   0.1708   1.0000
  14.000   1.6973   0.05461   0.04794  -0.1086   0.1622   1.0000
  14.250   1.6964   0.05752   0.05089  -0.1077   0.1544   1.0000
  14.500   1.6969   0.06036   0.05380  -0.1070   0.1462   1.0000
  14.750   1.6962   0.06342   0.05692  -0.1064   0.1389   1.0000
  15.000   1.6943   0.06670   0.06027  -0.1059   0.1316   1.0000
  15.250   1.6936   0.06992   0.06357  -0.1055   0.1247   1.0000
  15.500   1.6900   0.07358   0.06729  -0.1053   0.1182   1.0000
  15.750   1.6886   0.07702   0.07084  -0.1052   0.1117   1.0000
  16.000   1.6837   0.08104   0.07491  -0.1053   0.1057   1.0000
  16.250   1.6815   0.08474   0.07872  -0.1055   0.0998   1.0000
  16.500   1.6759   0.08902   0.08306  -0.1059   0.0942   1.0000
  16.750   1.6726   0.09300   0.08715  -0.1064   0.0890   1.0000
  17.000   1.6670   0.09739   0.09162  -0.1071   0.0839   1.0000
  17.250   1.6619   0.10178   0.09610  -0.1080   0.0794   1.0000
  17.500   1.6575   0.10611   0.10054  -0.1089   0.0747   1.0000
  17.750   1.6495   0.11107   0.10556  -0.1103   0.0709   1.0000
  18.000   1.6468   0.11519   0.10981  -0.1114   0.0667   1.0000
  18.250   1.6398   0.12005   0.11476  -0.1129   0.0629   1.0000
  18.500   1.6344   0.12471   0.11952  -0.1145   0.0595   1.0000
  18.750   1.6296   0.12927   0.12419  -0.1162   0.0558   1.0000
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