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EPPLER 432 AIRFOIL (e432-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 432 AIRFOIL (e432-il)
Reynolds number: 200,000
Max Cl/Cd: 75.42 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e432-il-200000-n5.txt
Download as CSV file: xf-e432-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.0535   0.09033   0.08662  -0.0957   0.8799   0.0171
 -11.000  -0.0456   0.08590   0.08211  -0.0985   0.8652   0.0166
 -10.750  -0.0424   0.08114   0.07729  -0.1010   0.8514   0.0159
 -10.250  -0.1494   0.08051   0.07676  -0.1008   0.8989   0.0142
 -10.000  -0.1331   0.07499   0.07116  -0.1080   0.8804   0.0140
  -9.750  -0.1283   0.06830   0.06438  -0.1151   0.8604   0.0137
  -9.500  -0.1394   0.05887   0.05483  -0.1241   0.8403   0.0133
  -9.250  -0.1622   0.05184   0.04758  -0.1285   0.8215   0.0130
  -9.000  -0.1882   0.04683   0.04231  -0.1287   0.8051   0.0127
  -8.750  -0.2150   0.04286   0.03805  -0.1260   0.7914   0.0125
  -8.500  -0.2328   0.03852   0.03328  -0.1234   0.7806   0.0122
  -8.250  -0.2457   0.03388   0.02805  -0.1203   0.7708   0.0119
  -8.000  -0.2447   0.03039   0.02397  -0.1180   0.7628   0.0117
  -7.750  -0.2331   0.02822   0.02142  -0.1164   0.7552   0.0118
  -7.500  -0.2173   0.02642   0.01925  -0.1153   0.7490   0.0118
  -7.250  -0.1991   0.02497   0.01756  -0.1143   0.7421   0.0120
  -7.000  -0.1789   0.02365   0.01596  -0.1134   0.7360   0.0122
  -6.750  -0.1575   0.02249   0.01458  -0.1127   0.7302   0.0124
  -6.500  -0.1354   0.02140   0.01331  -0.1119   0.7244   0.0128
  -6.250  -0.1124   0.02045   0.01216  -0.1113   0.7194   0.0132
  -6.000  -0.0894   0.01959   0.01114  -0.1106   0.7146   0.0136
  -5.750  -0.0667   0.01881   0.01023  -0.1098   0.7091   0.0143
  -5.500  -0.0439   0.01815   0.00950  -0.1092   0.7042   0.0149
  -5.250  -0.0200   0.01763   0.00889  -0.1088   0.7002   0.0160
  -5.000   0.0036   0.01715   0.00836  -0.1083   0.6953   0.0180
  -4.750   0.0277   0.01674   0.00791  -0.1078   0.6906   0.0203
  -4.500   0.0520   0.01629   0.00737  -0.1074   0.6864   0.0231
  -4.250   0.0767   0.01585   0.00687  -0.1071   0.6825   0.0271
  -4.000   0.1011   0.01546   0.00649  -0.1067   0.6781   0.0363
  -3.750   0.1259   0.01506   0.00613  -0.1064   0.6739   0.0512
  -3.500   0.1510   0.01466   0.00582  -0.1062   0.6701   0.0780
  -3.250   0.1762   0.01424   0.00556  -0.1062   0.6665   0.1243
  -3.000   0.2002   0.01370   0.00534  -0.1061   0.6622   0.2042
  -2.750   0.2239   0.01296   0.00511  -0.1062   0.6583   0.3402
  -2.500   0.2450   0.01209   0.00512  -0.1055   0.6547   0.5632
  -2.250   0.2685   0.01222   0.00546  -0.1040   0.6515   0.6712
  -2.000   0.2943   0.01240   0.00562  -0.1033   0.6475   0.7063
  -1.750   0.3209   0.01257   0.00572  -0.1029   0.6436   0.7283
  -1.500   0.3475   0.01274   0.00579  -0.1025   0.6399   0.7444
  -1.250   0.3732   0.01295   0.00592  -0.1017   0.6366   0.7582
  -1.000   0.3973   0.01324   0.00617  -0.1005   0.6332   0.7763
  -0.750   0.4189   0.01351   0.00645  -0.0987   0.6293   0.7909
  -0.500   0.4435   0.01364   0.00653  -0.0978   0.6256   0.7987
  -0.250   0.4703   0.01369   0.00650  -0.0977   0.6220   0.8027
   0.000   0.4992   0.01374   0.00643  -0.0981   0.6190   0.8065
   0.250   0.5276   0.01378   0.00642  -0.0985   0.6153   0.8104
   0.500   0.5537   0.01382   0.00644  -0.0983   0.6113   0.8126
   0.750   0.5804   0.01386   0.00644  -0.0982   0.6075   0.8149
   1.000   0.6081   0.01391   0.00642  -0.0983   0.6043   0.8175
   1.250   0.6362   0.01398   0.00643  -0.0986   0.6012   0.8200
   1.500   0.6630   0.01404   0.00650  -0.0987   0.5969   0.8230
   1.750   0.6911   0.01411   0.00653  -0.0991   0.5929   0.8261
   2.000   0.7184   0.01416   0.00656  -0.0992   0.5895   0.8282
   2.250   0.7463   0.01423   0.00657  -0.0994   0.5864   0.8301
   2.500   0.7714   0.01432   0.00670  -0.0991   0.5821   0.8324
   2.750   0.7973   0.01440   0.00681  -0.0990   0.5779   0.8352
   3.000   0.8245   0.01448   0.00688  -0.0991   0.5741   0.8381
   3.250   0.8534   0.01457   0.00691  -0.0996   0.5708   0.8408
   3.500   0.8793   0.01468   0.00707  -0.0996   0.5663   0.8434
   3.750   0.9039   0.01476   0.00721  -0.0991   0.5616   0.8455
   4.000   0.9297   0.01484   0.00729  -0.0990   0.5574   0.8479
   4.250   0.9562   0.01493   0.00737  -0.0989   0.5534   0.8508
   4.500   0.9802   0.01506   0.00758  -0.0985   0.5480   0.8541
   4.750   1.0062   0.01516   0.00771  -0.0985   0.5430   0.8573
   5.000   1.0332   0.01525   0.00777  -0.0986   0.5388   0.8598
   5.250   1.0546   0.01537   0.00801  -0.0976   0.5328   0.8625
   5.500   1.0782   0.01548   0.00816  -0.0971   0.5273   0.8655
   5.750   1.1035   0.01558   0.00827  -0.0968   0.5224   0.8689
   6.000   1.1257   0.01575   0.00853  -0.0961   0.5158   0.8729
   6.250   1.1487   0.01585   0.00868  -0.0955   0.5099   0.8763
   6.500   1.1700   0.01600   0.00889  -0.0945   0.5039   0.8799
   6.750   1.1910   0.01615   0.00911  -0.0935   0.4969   0.8839
   7.000   1.2137   0.01630   0.00929  -0.0929   0.4905   0.8881
   7.250   1.2323   0.01648   0.00957  -0.0915   0.4828   0.8923
   7.500   1.2520   0.01664   0.00975  -0.0902   0.4758   0.8972
   7.750   1.2691   0.01686   0.01008  -0.0886   0.4673   0.9033
   8.000   1.2844   0.01703   0.01029  -0.0866   0.4596   0.9096
   8.250   1.2979   0.01727   0.01062  -0.0843   0.4505   0.9175
   8.500   1.3108   0.01753   0.01094  -0.0819   0.4415   0.9266
   8.750   1.3235   0.01783   0.01129  -0.0796   0.4317   0.9393
   9.000   1.3380   0.01817   0.01172  -0.0779   0.4206   0.9649
   9.250   1.3530   0.01864   0.01222  -0.0765   0.4088   1.0000
   9.500   1.3665   0.01925   0.01284  -0.0750   0.3964   1.0000
   9.750   1.3777   0.01997   0.01357  -0.0733   0.3831   1.0000
  10.000   1.3869   0.02082   0.01441  -0.0713   0.3690   1.0000
  10.500   1.3997   0.02294   0.01651  -0.0672   0.3388   1.0000
  10.750   1.4036   0.02425   0.01780  -0.0651   0.3234   1.0000
  11.000   1.4060   0.02573   0.01927  -0.0630   0.3080   1.0000
  11.250   1.4074   0.02739   0.02090  -0.0611   0.2927   1.0000
  11.500   1.4078   0.02921   0.02270  -0.0592   0.2777   1.0000
  11.750   1.4081   0.03114   0.02462  -0.0576   0.2633   1.0000
  12.000   1.4078   0.03320   0.02667  -0.0561   0.2490   1.0000
  12.250   1.4080   0.03533   0.02880  -0.0547   0.2355   1.0000
  12.500   1.4078   0.03757   0.03105  -0.0536   0.2224   1.0000
  12.750   1.4076   0.03988   0.03337  -0.0525   0.2100   1.0000
  13.000   1.4070   0.04232   0.03580  -0.0516   0.1981   1.0000
  13.250   1.4057   0.04491   0.03840  -0.0507   0.1862   1.0000
  13.500   1.4046   0.04757   0.04105  -0.0501   0.1754   1.0000
  13.750   1.4049   0.05017   0.04368  -0.0495   0.1640   1.0000
  14.000   1.4050   0.05287   0.04640  -0.0491   0.1540   1.0000
  14.250   1.4037   0.05578   0.04934  -0.0488   0.1441   1.0000
  14.500   1.4025   0.05877   0.05234  -0.0486   0.1345   1.0000
  14.750   1.4030   0.06163   0.05524  -0.0485   0.1252   1.0000
  15.000   1.4019   0.06475   0.05839  -0.0485   0.1169   1.0000
  15.250   1.4002   0.06803   0.06169  -0.0487   0.1087   1.0000
  15.500   1.4006   0.07109   0.06481  -0.0489   0.1010   1.0000
  15.750   1.3983   0.07458   0.06833  -0.0493   0.0941   1.0000
  16.000   1.3981   0.07786   0.07167  -0.0497   0.0872   1.0000
  16.250   1.3965   0.08139   0.07526  -0.0502   0.0813   1.0000
  16.500   1.3951   0.08494   0.07887  -0.0509   0.0753   1.0000
  16.750   1.3933   0.08861   0.08260  -0.0516   0.0702   1.0000
  17.000   1.3915   0.09234   0.08640  -0.0524   0.0651   1.0000
  17.250   1.3890   0.09622   0.09034  -0.0534   0.0608   1.0000
  17.500   1.3872   0.10006   0.09426  -0.0545   0.0564   1.0000
  17.750   1.3829   0.10430   0.09856  -0.0558   0.0528   1.0000
  18.000   1.3821   0.10805   0.10242  -0.0569   0.0490   1.0000
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