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EPPLER 432 AIRFOIL (e432-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 432 AIRFOIL (e432-il)
Reynolds number: 200,000
Max Cl/Cd: 75.4 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e432-il-200000.txt
Download as CSV file: xf-e432-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1599   0.09714   0.09391  -0.0816   0.9599   0.0474
  -9.750  -0.1478   0.09189   0.08865  -0.0880   0.9489   0.0497
  -9.500  -0.1629   0.07910   0.07580  -0.1121   0.9343   0.0516
  -9.250  -0.1239   0.07814   0.07488  -0.1064   0.9306   0.0530
  -9.000  -0.0973   0.07460   0.07128  -0.1104   0.9194   0.0547
  -8.750  -0.0800   0.06879   0.06540  -0.1191   0.9049   0.0573
  -8.500  -0.0889   0.06103   0.05744  -0.1306   0.8832   0.0594
  -8.250  -0.1352   0.05817   0.05415  -0.1309   0.8583   0.0608
  -8.000  -0.1562   0.05691   0.05241  -0.1289   0.8435   0.0612
  -7.750  -0.1320   0.05088   0.04664  -0.1302   0.8361   0.0629
  -7.500  -0.1209   0.04873   0.04444  -0.1295   0.8265   0.0644
  -7.250  -0.1131   0.04659   0.04215  -0.1287   0.8181   0.0668
  -7.000  -0.1264   0.04459   0.03949  -0.1262   0.8082   0.0732
  -6.750  -0.1077   0.04142   0.03639  -0.1262   0.8019   0.0749
  -6.500  -0.1102   0.03126   0.02496  -0.1217   0.7955   0.0377
  -6.250  -0.0938   0.02721   0.02015  -0.1193   0.7889   0.0301
  -6.000  -0.0708   0.02508   0.01772  -0.1187   0.7838   0.0292
  -5.750  -0.0492   0.02335   0.01571  -0.1176   0.7775   0.0288
  -5.500  -0.0246   0.02187   0.01397  -0.1169   0.7719   0.0288
  -5.250   0.0022   0.02065   0.01249  -0.1164   0.7673   0.0296
  -5.000   0.0260   0.01982   0.01151  -0.1154   0.7614   0.0307
  -4.750   0.0493   0.01883   0.01059  -0.1148   0.7561   0.0332
  -4.500   0.0747   0.01816   0.00984  -0.1144   0.7518   0.0377
  -4.250   0.0975   0.01759   0.00929  -0.1136   0.7468   0.0426
  -4.000   0.1188   0.01685   0.00860  -0.1126   0.7413   0.0526
  -3.750   0.1418   0.01608   0.00794  -0.1121   0.7369   0.0767
  -3.500   0.1651   0.01520   0.00738  -0.1118   0.7332   0.1473
  -3.250   0.1806   0.01377   0.00707  -0.1111   0.7279   0.3848
  -3.000   0.1952   0.01332   0.00773  -0.1080   0.7232   0.6764
  -2.750   0.2204   0.01381   0.00812  -0.1065   0.7193   0.7287
  -2.500   0.2430   0.01438   0.00862  -0.1044   0.7154   0.7540
  -2.250   0.2631   0.01487   0.00908  -0.1020   0.7105   0.7743
  -2.000   0.2839   0.01531   0.00943  -0.0996   0.7061   0.7910
  -1.750   0.3059   0.01566   0.00969  -0.0974   0.7025   0.8046
  -1.500   0.3267   0.01598   0.00994  -0.0952   0.6987   0.8168
  -1.250   0.3455   0.01623   0.01015  -0.0930   0.6940   0.8293
  -1.000   0.3651   0.01646   0.01032  -0.0906   0.6897   0.8433
  -0.750   0.3837   0.01669   0.01048  -0.0876   0.6863   0.8588
  -0.500   0.4026   0.01687   0.01059  -0.0847   0.6829   0.8712
  -0.250   0.4198   0.01692   0.01066  -0.0824   0.6781   0.8798
   0.000   0.4431   0.01692   0.01059  -0.0817   0.6738   0.8866
   0.250   0.4699   0.01686   0.01043  -0.0817   0.6703   0.8914
   0.500   0.4983   0.01686   0.01033  -0.0819   0.6671   0.8949
   0.750   0.5166   0.01692   0.01042  -0.0805   0.6621   0.8997
   1.000   0.5411   0.01693   0.01038  -0.0804   0.6577   0.9041
   1.250   0.5689   0.01687   0.01025  -0.0806   0.6542   0.9070
   1.500   0.5997   0.01689   0.01016  -0.0814   0.6513   0.9098
   1.750   0.6170   0.01699   0.01033  -0.0799   0.6460   0.9138
   2.000   0.6416   0.01703   0.01035  -0.0798   0.6415   0.9177
   2.250   0.6705   0.01701   0.01028  -0.0803   0.6380   0.9204
   2.500   0.7020   0.01703   0.01020  -0.0813   0.6351   0.9227
   2.750   0.7185   0.01716   0.01044  -0.0796   0.6296   0.9272
   3.000   0.7433   0.01722   0.01049  -0.0795   0.6251   0.9309
   3.250   0.7733   0.01723   0.01047  -0.0803   0.6215   0.9338
   3.500   0.8051   0.01724   0.01040  -0.0813   0.6183   0.9361
   3.750   0.8207   0.01740   0.01069  -0.0794   0.6124   0.9410
   4.000   0.8468   0.01743   0.01071  -0.0795   0.6078   0.9452
   4.250   0.8785   0.01738   0.01063  -0.0805   0.6042   0.9482
   4.500   0.9040   0.01750   0.01079  -0.0805   0.5995   0.9520
   4.750   0.9261   0.01761   0.01097  -0.0799   0.5938   0.9568
   5.000   0.9567   0.01756   0.01092  -0.0807   0.5895   0.9609
   5.250   0.9937   0.01755   0.01084  -0.0827   0.5858   0.9640
   5.500   1.0133   0.01776   0.01121  -0.0819   0.5790   0.9706
   5.750   1.0475   0.01773   0.01120  -0.0835   0.5740   0.9744
   6.000   1.0874   0.01768   0.01109  -0.0861   0.5699   0.9772
   6.250   1.1118   0.01792   0.01150  -0.0864   0.5625   0.9842
   6.500   1.1504   0.01786   0.01145  -0.0889   0.5572   0.9882
   6.750   1.1844   0.01795   0.01159  -0.0907   0.5512   0.9967
   7.000   1.2016   0.01806   0.01179  -0.0893   0.5446   1.0000
   7.250   1.2348   0.01795   0.01163  -0.0906   0.5395   1.0000
   7.500   1.2515   0.01820   0.01203  -0.0894   0.5317   1.0000
   7.750   1.2823   0.01815   0.01198  -0.0904   0.5253   1.0000
   8.000   1.3048   0.01834   0.01227  -0.0901   0.5175   1.0000
   8.250   1.3335   0.01832   0.01226  -0.0907   0.5099   1.0000
   8.500   1.3550   0.01852   0.01257  -0.0902   0.5013   1.0000
   8.750   1.3835   0.01851   0.01255  -0.0907   0.4931   1.0000
   9.000   1.4002   0.01878   0.01294  -0.0894   0.4830   1.0000
   9.250   1.4229   0.01891   0.01311  -0.0890   0.4736   1.0000
   9.500   1.4401   0.01910   0.01334  -0.0876   0.4630   1.0000
   9.750   1.4506   0.01946   0.01378  -0.0851   0.4518   1.0000
  10.000   1.4636   0.01981   0.01416  -0.0831   0.4403   1.0000
  10.250   1.4756   0.02023   0.01459  -0.0810   0.4282   1.0000
  10.500   1.4848   0.02077   0.01512  -0.0786   0.4151   1.0000
  10.750   1.4893   0.02151   0.01591  -0.0757   0.4010   1.0000
  11.000   1.4929   0.02239   0.01681  -0.0728   0.3862   1.0000
  11.250   1.4952   0.02345   0.01787  -0.0701   0.3711   1.0000
  11.500   1.4960   0.02470   0.01911  -0.0673   0.3554   1.0000
  11.750   1.4954   0.02616   0.02055  -0.0647   0.3395   1.0000
  12.000   1.4936   0.02783   0.02219  -0.0623   0.3235   1.0000
  12.250   1.4907   0.02971   0.02405  -0.0600   0.3074   1.0000
  12.500   1.4873   0.03176   0.02609  -0.0579   0.2915   1.0000
  12.750   1.4836   0.03397   0.02827  -0.0561   0.2764   1.0000
  13.000   1.4795   0.03633   0.03061  -0.0544   0.2615   1.0000
  13.250   1.4752   0.03883   0.03308  -0.0529   0.2472   1.0000
  13.500   1.4708   0.04146   0.03569  -0.0516   0.2334   1.0000
  13.750   1.4669   0.04418   0.03843  -0.0506   0.2198   1.0000
  14.000   1.4631   0.04700   0.04125  -0.0497   0.2067   1.0000
  14.250   1.4594   0.04992   0.04418  -0.0490   0.1941   1.0000
  14.500   1.4555   0.05297   0.04724  -0.0485   0.1819   1.0000
  14.750   1.4513   0.05612   0.05039  -0.0480   0.1705   1.0000
  15.000   1.4460   0.05948   0.05371  -0.0477   0.1598   1.0000
  15.250   1.4423   0.06283   0.05709  -0.0476   0.1489   1.0000
  15.500   1.4392   0.06619   0.06049  -0.0477   0.1386   1.0000
  15.750   1.4349   0.06974   0.06405  -0.0478   0.1292   1.0000
  16.000   1.4290   0.07355   0.06783  -0.0480   0.1206   1.0000
  16.250   1.4266   0.07711   0.07148  -0.0485   0.1116   1.0000
  16.500   1.4224   0.08091   0.07530  -0.0489   0.1037   1.0000
  16.750   1.4171   0.08490   0.07927  -0.0496   0.0966   1.0000
  17.000   1.4146   0.08864   0.08311  -0.0503   0.0893   1.0000
  17.250   1.4091   0.09274   0.08714  -0.0511   0.0833   1.0000
  17.500   1.4069   0.09663   0.09117  -0.0521   0.0772   1.0000
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