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EPPLER 432 AIRFOIL (e432-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 432 AIRFOIL (e432-il)
Reynolds number: 1,000,000
Max Cl/Cd: 131.63 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e432-il-1000000-n5.txt
Download as CSV file: xf-e432-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4164   0.04062   0.03761  -0.1371   0.8195   0.0041
 -12.250  -0.4448   0.03600   0.03268  -0.1374   0.7923   0.0041
 -12.000  -0.4515   0.03379   0.03028  -0.1366   0.7739   0.0042
 -11.750  -0.4724   0.03059   0.02681  -0.1347   0.7594   0.0041
 -11.500  -0.4792   0.02867   0.02469  -0.1326   0.7472   0.0042
 -11.250  -0.4856   0.02686   0.02267  -0.1300   0.7359   0.0042
 -11.000  -0.4894   0.02538   0.02102  -0.1269   0.7266   0.0042
 -10.500  -0.4827   0.02310   0.01839  -0.1217   0.7096   0.0042
 -10.250  -0.4735   0.02187   0.01696  -0.1198   0.7020   0.0043
 -10.000  -0.4594   0.02088   0.01582  -0.1184   0.6961   0.0043
  -9.750  -0.4447   0.01982   0.01459  -0.1170   0.6899   0.0043
  -9.500  -0.4276   0.01897   0.01358  -0.1158   0.6836   0.0043
  -9.250  -0.4089   0.01813   0.01260  -0.1149   0.6783   0.0044
  -9.000  -0.3886   0.01747   0.01182  -0.1141   0.6728   0.0044
  -8.500  -0.3470   0.01603   0.01014  -0.1125   0.6638   0.0044
  -8.250  -0.3247   0.01544   0.00945  -0.1119   0.6590   0.0045
  -8.000  -0.3011   0.01503   0.00895  -0.1115   0.6544   0.0045
  -7.750  -0.2774   0.01460   0.00843  -0.1110   0.6501   0.0046
  -7.500  -0.2532   0.01415   0.00792  -0.1107   0.6464   0.0046
  -7.250  -0.2309   0.01342   0.00710  -0.1100   0.6424   0.0048
  -7.000  -0.2069   0.01295   0.00655  -0.1096   0.6384   0.0049
  -6.750  -0.1824   0.01256   0.00609  -0.1092   0.6344   0.0050
  -6.500  -0.1569   0.01218   0.00567  -0.1090   0.6312   0.0051
  -6.250  -0.1312   0.01185   0.00529  -0.1088   0.6279   0.0052
  -6.000  -0.1053   0.01155   0.00495  -0.1087   0.6243   0.0053
  -5.750  -0.0794   0.01128   0.00462  -0.1085   0.6207   0.0054
  -5.500  -0.0531   0.01102   0.00432  -0.1084   0.6174   0.0055
  -5.250  -0.0262   0.01077   0.00404  -0.1084   0.6144   0.0058
  -5.000   0.0008   0.01054   0.00378  -0.1083   0.6113   0.0060
  -4.750   0.0278   0.01034   0.00355  -0.1083   0.6078   0.0063
  -4.500   0.0548   0.01016   0.00333  -0.1083   0.6045   0.0067
  -4.250   0.0820   0.00998   0.00312  -0.1083   0.6015   0.0075
  -4.000   0.1097   0.00980   0.00293  -0.1084   0.5988   0.0092
  -3.750   0.1375   0.00964   0.00277  -0.1086   0.5958   0.0112
  -3.500   0.1651   0.00948   0.00262  -0.1087   0.5924   0.0159
  -3.250   0.1926   0.00934   0.00249  -0.1088   0.5891   0.0239
  -3.000   0.2202   0.00921   0.00238  -0.1089   0.5861   0.0343
  -2.750   0.2484   0.00903   0.00227  -0.1092   0.5835   0.0515
  -2.500   0.2763   0.00881   0.00217  -0.1095   0.5804   0.0840
  -2.250   0.3042   0.00856   0.00208  -0.1098   0.5771   0.1303
  -2.000   0.3320   0.00828   0.00199  -0.1102   0.5740   0.1966
  -1.750   0.3598   0.00802   0.00191  -0.1106   0.5707   0.2649
  -1.500   0.3885   0.00772   0.00184  -0.1111   0.5680   0.3450
  -1.250   0.4175   0.00719   0.00173  -0.1120   0.5648   0.4876
  -1.000   0.4466   0.00677   0.00172  -0.1127   0.5616   0.6291
  -0.750   0.4752   0.00676   0.00175  -0.1130   0.5582   0.6638
  -0.500   0.5035   0.00680   0.00178  -0.1132   0.5548   0.6812
  -0.250   0.5325   0.00683   0.00181  -0.1135   0.5519   0.6949
   0.000   0.5613   0.00687   0.00186  -0.1137   0.5487   0.7087
   0.250   0.5897   0.00693   0.00193  -0.1139   0.5450   0.7242
   0.500   0.6177   0.00700   0.00200  -0.1140   0.5413   0.7349
   0.750   0.6460   0.00708   0.00204  -0.1142   0.5380   0.7402
   1.000   0.6749   0.00712   0.00207  -0.1145   0.5347   0.7423
   1.250   0.7035   0.00717   0.00209  -0.1148   0.5308   0.7441
   1.500   0.7315   0.00723   0.00213  -0.1150   0.5268   0.7459
   1.750   0.7592   0.00731   0.00218  -0.1151   0.5227   0.7478
   2.000   0.7876   0.00735   0.00223  -0.1153   0.5187   0.7497
   2.250   0.8156   0.00742   0.00229  -0.1155   0.5139   0.7515
   2.500   0.8430   0.00751   0.00235  -0.1156   0.5089   0.7534
   2.750   0.8709   0.00758   0.00241  -0.1158   0.5043   0.7552
   3.000   0.8986   0.00766   0.00248  -0.1159   0.4987   0.7571
   3.250   0.9256   0.00777   0.00256  -0.1160   0.4931   0.7591
   3.500   0.9532   0.00786   0.00264  -0.1161   0.4878   0.7609
   3.750   0.9802   0.00794   0.00272  -0.1161   0.4817   0.7627
   4.000   1.0065   0.00806   0.00283  -0.1160   0.4757   0.7645
   4.250   1.0336   0.00815   0.00293  -0.1161   0.4696   0.7663
   4.500   1.0595   0.00829   0.00305  -0.1159   0.4627   0.7682
   4.750   1.0860   0.00840   0.00316  -0.1159   0.4561   0.7702
   5.000   1.1116   0.00855   0.00330  -0.1157   0.4482   0.7722
   5.250   1.1373   0.00869   0.00343  -0.1155   0.4408   0.7744
   5.500   1.1621   0.00887   0.00358  -0.1152   0.4320   0.7765
   5.750   1.1873   0.00902   0.00374  -0.1150   0.4236   0.7784
   6.000   1.2107   0.00923   0.00392  -0.1144   0.4134   0.7804
   6.250   1.2344   0.00942   0.00411  -0.1139   0.4027   0.7825
   6.500   1.2574   0.00964   0.00431  -0.1132   0.3918   0.7846
   6.750   1.2788   0.00992   0.00455  -0.1123   0.3782   0.7869
   7.000   1.2993   0.01021   0.00480  -0.1112   0.3643   0.7893
   7.250   1.3175   0.01054   0.00508  -0.1097   0.3486   0.7917
   7.500   1.3338   0.01088   0.00537  -0.1078   0.3334   0.7941
   7.750   1.3483   0.01128   0.00572  -0.1056   0.3166   0.7969
   8.000   1.3619   0.01173   0.00612  -0.1033   0.2994   0.7998
   8.250   1.3752   0.01221   0.00654  -0.1010   0.2835   0.8028
   8.500   1.3870   0.01274   0.00702  -0.0986   0.2669   0.8059
   8.750   1.3976   0.01334   0.00755  -0.0960   0.2501   0.8089
   9.000   1.4081   0.01394   0.00811  -0.0934   0.2352   0.8118
   9.250   1.4180   0.01458   0.00872  -0.0909   0.2210   0.8151
   9.500   1.4269   0.01529   0.00940  -0.0883   0.2072   0.8189
   9.750   1.4351   0.01608   0.01015  -0.0858   0.1938   0.8230
  10.250   1.4484   0.01793   0.01194  -0.0807   0.1679   0.8314
  10.500   1.4560   0.01889   0.01291  -0.0785   0.1587   0.8360
  10.750   1.4603   0.02010   0.01410  -0.0761   0.1464   0.8409
  11.000   1.4659   0.02131   0.01530  -0.0739   0.1358   0.8458
  11.250   1.4684   0.02278   0.01675  -0.0717   0.1234   0.8518
  11.500   1.4731   0.02419   0.01817  -0.0698   0.1140   0.8581
  11.750   1.4776   0.02567   0.01967  -0.0680   0.1063   0.8657
  12.250   1.4826   0.02907   0.02310  -0.0645   0.0878   0.8854
  12.500   1.4812   0.03110   0.02514  -0.0626   0.0771   0.9002
  12.750   1.4822   0.03282   0.02695  -0.0607   0.0710   0.9316
  13.250   1.4910   0.03672   0.03091  -0.0591   0.0587   1.0000
  13.500   1.4858   0.03959   0.03371  -0.0579   0.0469   1.0000
  13.750   1.4911   0.04157   0.03573  -0.0573   0.0441   1.0000
  14.000   1.4930   0.04394   0.03809  -0.0566   0.0389   1.0000
  14.250   1.4973   0.04612   0.04030  -0.0561   0.0353   1.0000
  14.500   1.4996   0.04856   0.04275  -0.0556   0.0318   1.0000
  14.750   1.5031   0.05093   0.04516  -0.0552   0.0286   1.0000
  15.000   1.5054   0.05347   0.04772  -0.0549   0.0253   1.0000
  15.250   1.5088   0.05596   0.05026  -0.0548   0.0232   1.0000
  15.500   1.5114   0.05859   0.05292  -0.0547   0.0210   1.0000
  15.750   1.5148   0.06115   0.05552  -0.0547   0.0190   1.0000
  16.000   1.5165   0.06399   0.05840  -0.0547   0.0173   1.0000
  16.250   1.5180   0.06690   0.06134  -0.0549   0.0150   1.0000
  16.500   1.5211   0.06967   0.06417  -0.0551   0.0143   1.0000
  16.750   1.5224   0.07270   0.06725  -0.0554   0.0126   1.0000
  17.000   1.5238   0.07576   0.07037  -0.0558   0.0115   1.0000
  17.250   1.5252   0.07889   0.07356  -0.0563   0.0105   1.0000
  17.500   1.5253   0.08224   0.07696  -0.0569   0.0093   1.0000
  17.750   1.5263   0.08552   0.08030  -0.0576   0.0086   1.0000
  18.000   1.5254   0.08909   0.08393  -0.0584   0.0075   1.0000
  18.250   1.5260   0.09247   0.08738  -0.0592   0.0070   1.0000
  18.500   1.5256   0.09609   0.09107  -0.0602   0.0063   1.0000
  18.750   1.5250   0.09975   0.09479  -0.0612   0.0058   1.0000
  19.000   1.5239   0.10353   0.09865  -0.0624   0.0053   1.0000
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