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EPPLER 432 AIRFOIL (e432-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 432 AIRFOIL (e432-il)
Reynolds number: 500,000
Max Cl/Cd: 108.34 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e432-il-500000-n5.txt
Download as CSV file: xf-e432-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1199   0.08623   0.08322  -0.1110   0.8510   0.0066
 -11.250  -0.1236   0.08167   0.07853  -0.1130   0.8247   0.0065
 -10.750  -0.2212   0.05210   0.04886  -0.1287   0.7944   0.0062
 -10.500  -0.2829   0.04105   0.03741  -0.1335   0.7780   0.0061
 -10.250  -0.3176   0.03624   0.03227  -0.1320   0.7638   0.0061
 -10.000  -0.3380   0.03324   0.02899  -0.1291   0.7516   0.0060
  -9.750  -0.3589   0.03046   0.02588  -0.1247   0.7412   0.0060
  -9.500  -0.3634   0.02798   0.02303  -0.1219   0.7326   0.0061
  -9.250  -0.3590   0.02595   0.02068  -0.1198   0.7247   0.0062
  -9.000  -0.3481   0.02446   0.01888  -0.1181   0.7178   0.0064
  -8.750  -0.3348   0.02297   0.01712  -0.1167   0.7114   0.0065
  -8.500  -0.3187   0.02175   0.01565  -0.1154   0.7048   0.0065
  -8.250  -0.3004   0.02071   0.01437  -0.1144   0.6992   0.0066
  -8.000  -0.2807   0.01974   0.01324  -0.1135   0.6934   0.0066
  -7.750  -0.2610   0.01867   0.01199  -0.1126   0.6882   0.0067
  -7.500  -0.2402   0.01778   0.01095  -0.1118   0.6835   0.0067
  -7.250  -0.2186   0.01693   0.00999  -0.1112   0.6787   0.0068
  -7.000  -0.1961   0.01627   0.00923  -0.1105   0.6736   0.0069
  -6.750  -0.1732   0.01570   0.00856  -0.1100   0.6691   0.0070
  -6.500  -0.1497   0.01515   0.00795  -0.1095   0.6652   0.0072
  -6.250  -0.1255   0.01467   0.00739  -0.1091   0.6610   0.0073
  -6.000  -0.1013   0.01422   0.00688  -0.1086   0.6567   0.0075
  -5.750  -0.0769   0.01382   0.00640  -0.1082   0.6526   0.0078
  -5.500  -0.0519   0.01343   0.00595  -0.1079   0.6490   0.0080
  -5.250  -0.0264   0.01307   0.00553  -0.1077   0.6453   0.0085
  -5.000  -0.0007   0.01275   0.00515  -0.1075   0.6416   0.0090
  -4.750   0.0249   0.01243   0.00479  -0.1072   0.6378   0.0097
  -4.500   0.0510   0.01219   0.00448  -0.1071   0.6344   0.0107
  -4.250   0.0776   0.01193   0.00420  -0.1070   0.6311   0.0121
  -4.000   0.1043   0.01168   0.00394  -0.1070   0.6276   0.0153
  -3.750   0.1310   0.01146   0.00372  -0.1070   0.6240   0.0208
  -3.500   0.1576   0.01125   0.00353  -0.1069   0.6206   0.0327
  -3.250   0.1845   0.01103   0.00337  -0.1070   0.6175   0.0498
  -3.000   0.2117   0.01078   0.00322  -0.1072   0.6144   0.0754
  -2.750   0.2388   0.01050   0.00309  -0.1074   0.6110   0.1152
  -2.500   0.2656   0.01015   0.00295  -0.1076   0.6075   0.1808
  -2.250   0.2925   0.00974   0.00281  -0.1080   0.6043   0.2726
  -2.000   0.3199   0.00925   0.00266  -0.1085   0.6015   0.3886
  -1.750   0.3477   0.00853   0.00255  -0.1093   0.5983   0.5676
  -1.500   0.3751   0.00840   0.00268  -0.1093   0.5948   0.6627
  -1.250   0.4032   0.00845   0.00273  -0.1093   0.5914   0.6894
  -1.000   0.4314   0.00852   0.00276  -0.1094   0.5884   0.7045
  -0.750   0.4596   0.00861   0.00280  -0.1095   0.5854   0.7168
  -0.500   0.4879   0.00868   0.00287  -0.1096   0.5820   0.7306
  -0.250   0.5154   0.00880   0.00300  -0.1094   0.5786   0.7474
   0.000   0.5429   0.00893   0.00310  -0.1093   0.5752   0.7583
   0.250   0.5711   0.00900   0.00311  -0.1095   0.5720   0.7622
   0.500   0.5992   0.00905   0.00313  -0.1096   0.5688   0.7642
   0.750   0.6274   0.00908   0.00316  -0.1098   0.5654   0.7663
   1.000   0.6556   0.00913   0.00319  -0.1100   0.5618   0.7684
   1.250   0.6836   0.00919   0.00322  -0.1102   0.5582   0.7704
   1.500   0.7114   0.00927   0.00325  -0.1104   0.5549   0.7728
   1.750   0.7398   0.00933   0.00329  -0.1106   0.5514   0.7751
   2.000   0.7681   0.00938   0.00334  -0.1109   0.5475   0.7771
   2.250   0.7956   0.00944   0.00339  -0.1110   0.5435   0.7788
   2.500   0.8227   0.00952   0.00345  -0.1110   0.5398   0.7804
   2.750   0.8501   0.00959   0.00353  -0.1111   0.5357   0.7823
   3.000   0.8774   0.00966   0.00361  -0.1112   0.5312   0.7844
   3.250   0.9043   0.00975   0.00368  -0.1112   0.5265   0.7866
   3.500   0.9310   0.00985   0.00377  -0.1112   0.5220   0.7887
   3.750   0.9583   0.00992   0.00387  -0.1113   0.5169   0.7909
   4.000   0.9849   0.01002   0.00396  -0.1113   0.5115   0.7930
   4.250   1.0109   0.01014   0.00406  -0.1111   0.5065   0.7949
   4.500   1.0372   0.01022   0.00419  -0.1110   0.5009   0.7968
   4.750   1.0624   0.01034   0.00431  -0.1108   0.4949   0.7989
   5.000   1.0878   0.01046   0.00445  -0.1105   0.4893   0.8013
   5.250   1.1133   0.01058   0.00460  -0.1103   0.4829   0.8036
   5.500   1.1374   0.01075   0.00475  -0.1098   0.4765   0.8060
   5.750   1.1629   0.01087   0.00491  -0.1096   0.4695   0.8084
   6.250   1.2102   0.01120   0.00527  -0.1086   0.4544   0.8127
   6.500   1.2318   0.01141   0.00547  -0.1077   0.4462   0.8151
   6.750   1.2546   0.01158   0.00569  -0.1070   0.4374   0.8179
   7.000   1.2751   0.01182   0.00593  -0.1059   0.4281   0.8209
   7.250   1.2948   0.01205   0.00617  -0.1047   0.4178   0.8240
   7.750   1.3285   0.01261   0.00673  -0.1011   0.3952   0.8298
   8.000   1.3431   0.01298   0.00709  -0.0990   0.3823   0.8330
   8.250   1.3569   0.01340   0.00750  -0.0968   0.3688   0.8366
   8.500   1.3700   0.01387   0.00795  -0.0946   0.3543   0.8405
   8.750   1.3809   0.01442   0.00848  -0.0921   0.3384   0.8445
   9.000   1.3901   0.01503   0.00908  -0.0894   0.3220   0.8490
   9.250   1.3986   0.01573   0.00975  -0.0867   0.3062   0.8541
   9.750   1.4108   0.01743   0.01141  -0.0810   0.2741   0.8646
  10.000   1.4152   0.01845   0.01241  -0.0782   0.2585   0.8712
  10.250   1.4191   0.01955   0.01350  -0.0755   0.2442   0.8781
  10.500   1.4220   0.02076   0.01471  -0.0728   0.2301   0.8872
  10.750   1.4242   0.02205   0.01602  -0.0702   0.2173   0.8985
  11.000   1.4255   0.02342   0.01741  -0.0676   0.2044   0.9153
  11.250   1.4288   0.02487   0.01891  -0.0658   0.1910   0.9705
  11.750   1.4369   0.02821   0.02223  -0.0628   0.1685   1.0000
  12.000   1.4397   0.03010   0.02410  -0.0614   0.1576   1.0000
  12.250   1.4414   0.03214   0.02612  -0.0601   0.1463   1.0000
  12.500   1.4438   0.03418   0.02816  -0.0590   0.1355   1.0000
  12.750   1.4461   0.03630   0.03026  -0.0580   0.1253   1.0000
  13.000   1.4484   0.03846   0.03243  -0.0570   0.1167   1.0000
  13.500   1.4536   0.04292   0.03690  -0.0555   0.1007   1.0000
  13.750   1.4549   0.04537   0.03936  -0.0549   0.0932   1.0000
  14.000   1.4568   0.04782   0.04182  -0.0543   0.0859   1.0000
  14.250   1.4595   0.05023   0.04426  -0.0539   0.0797   1.0000
  14.500   1.4598   0.05296   0.04699  -0.0535   0.0730   1.0000
  14.750   1.4622   0.05554   0.04960  -0.0533   0.0670   1.0000
  15.000   1.4630   0.05833   0.05242  -0.0531   0.0616   1.0000
  15.250   1.4646   0.06111   0.05522  -0.0531   0.0561   1.0000
  15.500   1.4654   0.06403   0.05818  -0.0531   0.0516   1.0000
  15.750   1.4664   0.06699   0.06118  -0.0532   0.0470   1.0000
  16.000   1.4671   0.07004   0.06427  -0.0534   0.0431   1.0000
  16.250   1.4658   0.07340   0.06764  -0.0537   0.0387   1.0000
  16.500   1.4683   0.07633   0.07065  -0.0541   0.0365   1.0000
  16.750   1.4668   0.07985   0.07420  -0.0546   0.0326   1.0000
  17.000   1.4670   0.08320   0.07761  -0.0552   0.0299   1.0000
  17.250   1.4668   0.08662   0.08109  -0.0559   0.0275   1.0000
  17.500   1.4654   0.09028   0.08481  -0.0567   0.0249   1.0000
  17.750   1.4649   0.09387   0.08846  -0.0576   0.0230   1.0000
  18.000   1.4629   0.09772   0.09237  -0.0586   0.0207   1.0000
  18.250   1.4615   0.10152   0.09624  -0.0597   0.0190   1.0000
  18.500   1.4594   0.10546   0.10024  -0.0609   0.0174   1.0000
  18.750   1.4579   0.10933   0.10419  -0.0622   0.0159   1.0000
  19.000   1.4549   0.11349   0.10842  -0.0637   0.0147   1.0000
  19.250   1.4533   0.11745   0.11246  -0.0651   0.0133   1.0000
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