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EPPLER 432 AIRFOIL (e432-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 432 AIRFOIL (e432-il)
Reynolds number: 100,000
Max Cl/Cd: 36.7 at α=12°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e432-il-100000.txt
Download as CSV file: xf-e432-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 432 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.2508   0.13193   0.12733  -0.0496   1.0000   0.0784
 -11.250  -0.2625   0.13112   0.12666  -0.0470   1.0000   0.0799
 -11.000  -0.2929   0.13300   0.12874  -0.0405   1.0000   0.0801
 -10.750  -0.2930   0.13013   0.12591  -0.0453   0.9958   0.0833
 -10.500  -0.3030   0.12628   0.12211  -0.0585   0.9874   0.0849
 -10.250  -0.2591   0.11974   0.11553  -0.0561   0.9855   0.0876
 -10.000  -0.2352   0.11549   0.11125  -0.0598   0.9796   0.0913
  -9.750  -0.2244   0.11097   0.10673  -0.0671   0.9732   0.0967
  -9.500  -0.2493   0.10619   0.10202  -0.0832   0.9604   0.0988
  -9.250  -0.1929   0.10126   0.09702  -0.0767   0.9603   0.1028
  -9.000  -0.1760   0.09738   0.09313  -0.0803   0.9524   0.1077
  -8.750  -0.2063   0.09181   0.08762  -0.0963   0.9380   0.1132
  -8.500  -0.1583   0.08766   0.08344  -0.0923   0.9373   0.1171
  -8.250  -0.1370   0.08334   0.07910  -0.0973   0.9324   0.1245
  -8.000  -0.1936   0.07824   0.07383  -0.1121   0.9135   0.1288
  -7.750  -0.0154   0.05989   0.05574  -0.1118   0.8996   0.1547
  -7.500  -0.0465   0.05615   0.05203  -0.1144   0.8869   0.1584
  -7.250  -0.0302   0.05210   0.04797  -0.1155   0.8828   0.1698
  -7.000  -0.0602   0.05016   0.04603  -0.1139   0.8698   0.1726
  -6.750  -0.1130   0.04905   0.04471  -0.1119   0.8555   0.1768
  -6.250  -0.1685   0.04706   0.04061  -0.1139   0.8544   0.0730
  -6.000  -0.1412   0.04166   0.03474  -0.1145   0.8509   0.0598
  -5.750  -0.1379   0.04016   0.03303  -0.1113   0.8417   0.0590
  -5.500  -0.1133   0.03749   0.02993  -0.1113   0.8369   0.0584
  -5.250  -0.0799   0.03480   0.02672  -0.1123   0.8338   0.0591
  -5.000  -0.0762   0.03408   0.02578  -0.1085   0.8244   0.0589
  -4.750  -0.0441   0.03200   0.02332  -0.1088   0.8204   0.0594
  -4.500  -0.0068   0.02996   0.02095  -0.1098   0.8176   0.0620
  -4.000   0.0263   0.02866   0.01964  -0.1061   0.8045   0.0742
  -3.750   0.0608   0.02723   0.01831  -0.1069   0.8016   0.0893
  -3.500   0.0637   0.02732   0.01850  -0.1032   0.7936   0.1028
  -3.250   0.0834   0.02649   0.01790  -0.1019   0.7884   0.1418
  -3.000   0.0993   0.02348   0.01699  -0.1007   0.7852   0.4816
  -2.750   0.0812   0.02497   0.01927  -0.0907   0.7764   0.7000
  -2.500   0.0862   0.02627   0.02048  -0.0841   0.7710   0.7703
  -2.250   0.1003   0.02704   0.02109  -0.0780   0.7681   0.8134
  -2.000   0.0780   0.02848   0.02256  -0.0703   0.7576   0.8290
  -1.750   0.0853   0.02897   0.02293  -0.0642   0.7535   0.8598
  -1.500   0.1092   0.02910   0.02289  -0.0602   0.7512   0.8914
  -1.250   0.3692   0.02810   0.02107  -0.0968   0.7560   0.9519
  -1.000   0.4465   0.02731   0.02002  -0.1061   0.7536   0.9654
  -0.750   0.4994   0.02677   0.01927  -0.1111   0.7509   0.9736
  -0.500   0.5135   0.02770   0.02021  -0.1108   0.7428   0.9822
  -0.250   0.5563   0.02751   0.01989  -0.1145   0.7384   0.9880
   0.000   0.6022   0.02706   0.01930  -0.1182   0.7353   0.9928
   0.250   0.6194   0.02795   0.02020  -0.1183   0.7281   0.9986
   0.500   0.6322   0.02851   0.02072  -0.1168   0.7222   1.0000
   0.750   0.6587   0.02838   0.02051  -0.1168   0.7188   1.0000
   1.000   0.6197   0.03076   0.02299  -0.1076   0.7083   1.0000
   1.250   0.6363   0.03098   0.02315  -0.1062   0.7039   1.0000
   1.500   0.6712   0.03058   0.02267  -0.1073   0.7015   1.0000
   1.750   0.5871   0.03419   0.02641  -0.0918   0.6878   1.0000
   2.000   0.6249   0.03374   0.02588  -0.0932   0.6855   1.0000
   2.250   0.4907   0.03799   0.03027  -0.0712   0.6697   1.0000
   2.500   0.5390   0.03730   0.02949  -0.0737   0.6683   1.0000
   2.750   0.4368   0.04089   0.03317  -0.0582   0.6537   1.0000
   3.000   0.4220   0.04302   0.03529  -0.0551   0.6447   1.0000
   3.250   0.4463   0.04363   0.03585  -0.0555   0.6393   1.0000
   3.500   0.4889   0.04340   0.03556  -0.0573   0.6365   1.0000
   3.750   0.4768   0.04612   0.03829  -0.0555   0.6257   1.0000
   4.000   0.5133   0.04624   0.03837  -0.0569   0.6216   1.0000
   4.250   0.5605   0.04575   0.03783  -0.0589   0.6193   1.0000
   4.500   0.5443   0.04896   0.04106  -0.0572   0.6072   1.0000
   4.750   0.5882   0.04861   0.04069  -0.0588   0.6041   1.0000
   5.000   0.5806   0.05145   0.04355  -0.0577   0.5929   1.0000
   5.250   0.6202   0.05128   0.04337  -0.0590   0.5890   1.0000
   5.500   0.6222   0.05359   0.04570  -0.0584   0.5791   1.0000
   5.750   0.6550   0.05379   0.04590  -0.0592   0.5738   1.0000
   6.000   0.7017   0.05302   0.04514  -0.0607   0.5713   1.0000
   6.250   0.6912   0.05619   0.04834  -0.0594   0.5587   1.0000
   6.500   0.7375   0.05527   0.04744  -0.0606   0.5559   1.0000
   6.750   0.7301   0.05828   0.05048  -0.0596   0.5435   1.0000
   7.000   0.7745   0.05738   0.04962  -0.0605   0.5405   1.0000
   7.250   0.8249   0.05591   0.04820  -0.0617   0.5388   1.0000
   7.500   0.8134   0.05922   0.05155  -0.0604   0.5251   1.0000
   7.750   0.8590   0.05794   0.05033  -0.0611   0.5226   1.0000
   8.000   0.8529   0.06089   0.05332  -0.0600   0.5097   1.0000
   8.250   0.8499   0.06370   0.05618  -0.0592   0.4973   1.0000
   8.500   0.8942   0.06222   0.05477  -0.0596   0.4943   1.0000
   8.750   0.9453   0.05990   0.05256  -0.0601   0.4927   1.0000
   9.750   1.0166   0.06256   0.05553  -0.0580   0.4591   1.0000
  10.000   1.0830   0.05764   0.05077  -0.0581   0.4603   1.0000
  10.250   1.1476   0.05273   0.04601  -0.0582   0.4604   1.0000
  10.500   1.2264   0.04690   0.04036  -0.0593   0.4601   1.0000
  10.750   1.2268   0.04857   0.04212  -0.0576   0.4479   1.0000
  11.000   1.3731   0.03806   0.03178  -0.0636   0.4467   1.0000
  11.250   1.3576   0.04034   0.03415  -0.0600   0.4338   1.0000
  11.500   1.3744   0.04037   0.03428  -0.0587   0.4214   1.0000
  11.750   1.4068   0.03923   0.03319  -0.0584   0.4081   1.0000
  12.000   1.4288   0.03893   0.03292  -0.0575   0.3937   1.0000
  12.250   1.4421   0.03931   0.03333  -0.0561   0.3785   1.0000
  12.500   1.4504   0.04013   0.03416  -0.0544   0.3627   1.0000
  12.750   1.4555   0.04128   0.03531  -0.0527   0.3466   1.0000
  13.000   1.4586   0.04268   0.03670  -0.0510   0.3304   1.0000
  13.250   1.4606   0.04429   0.03828  -0.0494   0.3141   1.0000
  13.500   1.4614   0.04609   0.04005  -0.0479   0.2980   1.0000
  13.750   1.4610   0.04809   0.04203  -0.0465   0.2821   1.0000
  14.000   1.4596   0.05031   0.04421  -0.0453   0.2667   1.0000
  14.250   1.4570   0.05273   0.04661  -0.0441   0.2518   1.0000
  14.500   1.4534   0.05535   0.04921  -0.0431   0.2373   1.0000
  14.750   1.4498   0.05811   0.05196  -0.0423   0.2234   1.0000
  15.000   1.4460   0.06099   0.05484  -0.0416   0.2100   1.0000
  15.250   1.4425   0.06394   0.05777  -0.0411   0.1972   1.0000
  15.500   1.4398   0.06689   0.06069  -0.0407   0.1848   1.0000
  15.750   1.4385   0.06976   0.06351  -0.0403   0.1728   1.0000
  16.000   1.4384   0.07254   0.06622  -0.0401   0.1609   1.0000
  16.250   1.4276   0.07680   0.07066  -0.0403   0.1514   1.0000
  16.500   1.4245   0.08021   0.07409  -0.0405   0.1415   1.0000
  16.750   1.4255   0.08307   0.07687  -0.0405   0.1317   1.0000
  17.000   1.4196   0.08697   0.08088  -0.0410   0.1234   1.0000
  17.250   1.4161   0.09068   0.08466  -0.0415   0.1155   1.0000
  17.500   1.4229   0.09288   0.08671  -0.0415   0.1068   1.0000
  17.750   1.4112   0.09791   0.09203  -0.0427   0.1014   1.0000
  18.000   1.4180   0.10018   0.09418  -0.0429   0.0940   1.0000
  18.250   1.4072   0.10521   0.09949  -0.0444   0.0895   1.0000
  18.500   1.4180   0.10692   0.10106  -0.0444   0.0828   1.0000
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