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EPPLER 432 AIRFOIL (e432-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 432 AIRFOIL (e432-il)
Reynolds number: 1,000,000
Max Cl/Cd: 141.36 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e432-il-1000000.txt
Download as CSV file: xf-e432-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.0466   0.07323   0.07072  -0.1079   0.7730   0.0116
 -10.750  -0.0437   0.07060   0.06805  -0.1085   0.7622   0.0118
 -10.500  -0.0414   0.06768   0.06508  -0.1093   0.7520   0.0120
 -10.250  -0.0445   0.06331   0.06070  -0.1109   0.7442   0.0121
 -10.000  -0.0494   0.05865   0.05601  -0.1126   0.7367   0.0122
  -9.750  -0.0634   0.05193   0.04929  -0.1156   0.7310   0.0122
  -9.500  -0.1499   0.03145   0.02864  -0.1285   0.7308   0.0119
  -9.250  -0.1874   0.02648   0.02346  -0.1280   0.7237   0.0119
  -9.000  -0.1798   0.02698   0.02396  -0.1270   0.7157   0.0121
  -8.750  -0.2116   0.02368   0.02047  -0.1231   0.7090   0.0121
  -8.500  -0.2972   0.02391   0.01941  -0.1197   0.7151   0.0084
  -8.250  -0.2878   0.02152   0.01669  -0.1178   0.7083   0.0083
  -8.000  -0.2716   0.02007   0.01498  -0.1165   0.7021   0.0083
  -7.750  -0.2537   0.01848   0.01316  -0.1154   0.6968   0.0082
  -7.500  -0.2333   0.01723   0.01171  -0.1145   0.6914   0.0082
  -7.250  -0.2121   0.01611   0.01038  -0.1137   0.6861   0.0081
  -7.000  -0.1891   0.01525   0.00939  -0.1131   0.6815   0.0081
  -6.750  -0.1656   0.01447   0.00850  -0.1125   0.6767   0.0081
  -6.500  -0.1415   0.01389   0.00782  -0.1121   0.6722   0.0083
  -6.250  -0.1168   0.01350   0.00732  -0.1116   0.6676   0.0085
  -6.000  -0.0917   0.01297   0.00674  -0.1113   0.6640   0.0086
  -5.750  -0.0668   0.01246   0.00617  -0.1110   0.6599   0.0087
  -5.500  -0.0420   0.01199   0.00564  -0.1106   0.6558   0.0088
  -5.250  -0.0170   0.01161   0.00517  -0.1102   0.6517   0.0088
  -5.000   0.0082   0.01109   0.00461  -0.1100   0.6486   0.0090
  -4.750   0.0339   0.01062   0.00410  -0.1098   0.6449   0.0093
  -4.500   0.0604   0.01031   0.00376  -0.1097   0.6413   0.0099
  -4.250   0.0872   0.01009   0.00350  -0.1096   0.6376   0.0105
  -4.000   0.1141   0.00983   0.00319  -0.1096   0.6341   0.0128
  -3.750   0.1416   0.00957   0.00294  -0.1096   0.6311   0.0174
  -3.500   0.1689   0.00926   0.00273  -0.1097   0.6278   0.0364
  -3.250   0.1964   0.00905   0.00259  -0.1099   0.6243   0.0562
  -3.000   0.2238   0.00886   0.00247  -0.1101   0.6209   0.0842
  -2.750   0.2514   0.00860   0.00236  -0.1104   0.6176   0.1320
  -2.250   0.3066   0.00740   0.00207  -0.1117   0.6115   0.4036
  -2.000   0.3348   0.00660   0.00198  -0.1125   0.6083   0.6350
  -1.750   0.3634   0.00661   0.00202  -0.1127   0.6049   0.6760
  -1.500   0.3922   0.00667   0.00205  -0.1130   0.6015   0.6946
  -1.250   0.4213   0.00670   0.00208  -0.1132   0.5987   0.7103
  -1.000   0.4500   0.00674   0.00212  -0.1134   0.5956   0.7213
  -0.750   0.4789   0.00680   0.00214  -0.1136   0.5923   0.7296
  -0.500   0.5071   0.00688   0.00219  -0.1137   0.5889   0.7364
  -0.250   0.5359   0.00699   0.00224  -0.1140   0.5855   0.7433
   0.000   0.5643   0.00702   0.00231  -0.1141   0.5827   0.7504
   0.250   0.5927   0.00713   0.00240  -0.1142   0.5794   0.7596
   0.500   0.6203   0.00720   0.00249  -0.1141   0.5761   0.7672
   0.750   0.6482   0.00731   0.00256  -0.1142   0.5726   0.7722
   1.000   0.6768   0.00738   0.00260  -0.1145   0.5691   0.7747
   1.250   0.7057   0.00740   0.00262  -0.1148   0.5659   0.7767
   1.500   0.7344   0.00743   0.00263  -0.1151   0.5624   0.7785
   1.750   0.7623   0.00746   0.00264  -0.1153   0.5586   0.7805
   2.000   0.7899   0.00755   0.00269  -0.1154   0.5543   0.7823
   2.250   0.8184   0.00757   0.00273  -0.1157   0.5509   0.7842
   2.500   0.8465   0.00760   0.00278  -0.1159   0.5468   0.7862
   2.750   0.8742   0.00767   0.00282  -0.1160   0.5425   0.7882
   3.000   0.9017   0.00777   0.00289  -0.1162   0.5380   0.7902
   3.250   0.9301   0.00780   0.00294  -0.1165   0.5339   0.7920
   3.500   0.9579   0.00787   0.00300  -0.1167   0.5291   0.7937
   3.750   0.9846   0.00795   0.00306  -0.1166   0.5243   0.7958
   4.000   1.0121   0.00799   0.00313  -0.1168   0.5199   0.7980
   4.250   1.0394   0.00805   0.00321  -0.1169   0.5148   0.7999
   4.500   1.0658   0.00816   0.00330  -0.1168   0.5096   0.8020
   4.750   1.0928   0.00824   0.00340  -0.1168   0.5046   0.8040
   5.000   1.1198   0.00832   0.00350  -0.1169   0.4988   0.8062
   5.250   1.1453   0.00846   0.00361  -0.1167   0.4929   0.8083
   5.500   1.1725   0.00854   0.00371  -0.1168   0.4873   0.8102
   5.750   1.1982   0.00864   0.00382  -0.1166   0.4808   0.8126
   6.000   1.2232   0.00877   0.00396  -0.1163   0.4743   0.8150
   6.250   1.2487   0.00888   0.00409  -0.1161   0.4672   0.8173
   6.500   1.2728   0.00904   0.00425  -0.1157   0.4599   0.8198
   6.750   1.2977   0.00918   0.00440  -0.1154   0.4514   0.8223
   7.000   1.3212   0.00936   0.00458  -0.1148   0.4430   0.8247
   7.250   1.3445   0.00956   0.00476  -0.1143   0.4332   0.8269
   7.500   1.3672   0.00972   0.00495  -0.1136   0.4235   0.8298
   7.750   1.3878   0.00996   0.00518  -0.1125   0.4123   0.8326
   8.000   1.4063   0.01023   0.00543  -0.1110   0.4001   0.8358
   8.250   1.4241   0.01049   0.00568  -0.1094   0.3869   0.8392
   8.500   1.4396   0.01085   0.00599  -0.1074   0.3715   0.8425
   8.750   1.4537   0.01123   0.00634  -0.1052   0.3555   0.8462
   9.000   1.4661   0.01169   0.00676  -0.1027   0.3389   0.8501
   9.250   1.4779   0.01220   0.00722  -0.1002   0.3209   0.8543
   9.500   1.4880   0.01279   0.00775  -0.0975   0.3019   0.8586
   9.750   1.4955   0.01345   0.00836  -0.0944   0.2833   0.8636
  10.000   1.5024   0.01417   0.00904  -0.0914   0.2663   0.8695
  10.250   1.5093   0.01494   0.00977  -0.0886   0.2508   0.8756
  10.500   1.5141   0.01580   0.01061  -0.0855   0.2353   0.8829
  10.750   1.5173   0.01681   0.01158  -0.0824   0.2193   0.8913
  11.000   1.5205   0.01785   0.01262  -0.0794   0.2051   0.9023
  11.250   1.5219   0.01899   0.01376  -0.0763   0.1912   0.9189
  11.500   1.5237   0.02012   0.01496  -0.0736   0.1781   1.0000
  11.750   1.5290   0.02150   0.01631  -0.0718   0.1662   1.0000
  12.000   1.5312   0.02314   0.01790  -0.0698   0.1528   1.0000
  12.250   1.5331   0.02488   0.01960  -0.0679   0.1404   1.0000
  12.500   1.5325   0.02688   0.02154  -0.0660   0.1265   1.0000
  12.750   1.5340   0.02880   0.02344  -0.0645   0.1163   1.0000
  13.000   1.5352   0.03083   0.02544  -0.0630   0.1071   1.0000
  13.250   1.5359   0.03295   0.02754  -0.0617   0.0974   1.0000
  13.500   1.5335   0.03542   0.02996  -0.0603   0.0859   1.0000
  13.750   1.5370   0.03745   0.03201  -0.0594   0.0795   1.0000
  14.000   1.5372   0.03983   0.03437  -0.0584   0.0723   1.0000
  14.250   1.5396   0.04208   0.03664  -0.0577   0.0662   1.0000
  14.500   1.5413   0.04446   0.03903  -0.0570   0.0609   1.0000
  14.750   1.5413   0.04707   0.04164  -0.0564   0.0549   1.0000
  15.000   1.5433   0.04953   0.04411  -0.0559   0.0496   1.0000
  15.250   1.5431   0.05229   0.04689  -0.0555   0.0449   1.0000
  15.500   1.5455   0.05485   0.04948  -0.0553   0.0412   1.0000
  15.750   1.5462   0.05764   0.05228  -0.0551   0.0375   1.0000
  16.000   1.5481   0.06035   0.05503  -0.0550   0.0344   1.0000
  16.250   1.5475   0.06341   0.05811  -0.0550   0.0309   1.0000
  16.500   1.5506   0.06609   0.06085  -0.0551   0.0288   1.0000
  16.750   1.5490   0.06941   0.06420  -0.0553   0.0259   1.0000
  17.000   1.5507   0.07237   0.06721  -0.0556   0.0238   1.0000
  17.250   1.5496   0.07572   0.07059  -0.0560   0.0218   1.0000
  17.500   1.5506   0.07888   0.07382  -0.0565   0.0201   1.0000
  17.750   1.5499   0.08231   0.07728  -0.0571   0.0184   1.0000
  18.000   1.5498   0.08572   0.08076  -0.0578   0.0170   1.0000
  18.250   1.5492   0.08922   0.08432  -0.0586   0.0157   1.0000
  18.500   1.5475   0.09293   0.08808  -0.0594   0.0145   1.0000
  18.750   1.5471   0.09652   0.09174  -0.0604   0.0136   1.0000
  19.000   1.5457   0.10028   0.09558  -0.0615   0.0127   1.0000
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