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EPPLER 434 AIRFOIL (e434-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 434 AIRFOIL (e434-il)
Reynolds number: 200,000
Max Cl/Cd: 80.78 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e434-il-200000-n5.txt
Download as CSV file: xf-e434-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 434 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1184   0.07068   0.06674  -0.1062   0.8627   0.0127
  -8.500  -0.1172   0.06734   0.06336  -0.1082   0.8526   0.0124
  -8.250  -0.1198   0.06365   0.05966  -0.1108   0.8426   0.0122
  -8.000  -0.1301   0.05947   0.05541  -0.1132   0.8332   0.0120
  -7.750  -0.1392   0.05601   0.05187  -0.1137   0.8246   0.0116
  -7.500  -0.1636   0.04625   0.04176  -0.1144   0.8172   0.0100
  -7.250  -0.1614   0.04331   0.03865  -0.1136   0.8107   0.0099
  -7.000  -0.1553   0.04052   0.03563  -0.1127   0.8055   0.0098
  -6.750  -0.1494   0.03712   0.03196  -0.1115   0.8003   0.0096
  -6.500  -0.1412   0.03374   0.02825  -0.1100   0.7951   0.0094
  -6.250  -0.1302   0.03038   0.02446  -0.1084   0.7907   0.0093
  -6.000  -0.1157   0.02736   0.02094  -0.1069   0.7868   0.0091
  -5.750  -0.0987   0.02477   0.01790  -0.1054   0.7820   0.0091
  -5.500  -0.0781   0.02268   0.01538  -0.1043   0.7779   0.0091
  -5.250  -0.0551   0.02091   0.01319  -0.1034   0.7745   0.0094
  -5.000  -0.0309   0.01960   0.01159  -0.1027   0.7711   0.0096
  -4.750  -0.0070   0.01847   0.01022  -0.1019   0.7667   0.0100
  -4.500   0.0170   0.01765   0.00932  -0.1014   0.7628   0.0105
  -4.250   0.0420   0.01702   0.00859  -0.1010   0.7595   0.0115
  -4.000   0.0676   0.01651   0.00798  -0.1007   0.7564   0.0137
  -3.750   0.0916   0.01603   0.00746  -0.1001   0.7522   0.0153
  -3.500   0.1159   0.01547   0.00683  -0.0995   0.7482   0.0170
  -3.250   0.1412   0.01503   0.00630  -0.0991   0.7448   0.0193
  -3.000   0.1672   0.01461   0.00583  -0.0988   0.7418   0.0251
  -2.750   0.1913   0.01416   0.00546  -0.0982   0.7379   0.0417
  -2.500   0.2153   0.01368   0.00520  -0.0978   0.7339   0.0896
  -2.250   0.2388   0.01310   0.00499  -0.0975   0.7303   0.1876
  -2.000   0.2605   0.01226   0.00480  -0.0969   0.7271   0.3711
  -1.750   0.2757   0.01129   0.00486  -0.0946   0.7236   0.6399
  -1.500   0.2931   0.01134   0.00524  -0.0915   0.7194   0.7811
  -1.250   0.3161   0.01148   0.00533  -0.0900   0.7156   0.8201
  -1.000   0.3397   0.01161   0.00537  -0.0887   0.7124   0.8449
  -0.750   0.3631   0.01173   0.00541  -0.0873   0.7091   0.8631
  -0.500   0.3831   0.01187   0.00553  -0.0853   0.7046   0.8816
  -0.250   0.4004   0.01203   0.00566  -0.0822   0.7006   0.9065
   0.000   0.4236   0.01211   0.00568  -0.0804   0.6972   0.9264
   0.250   0.4507   0.01213   0.00560  -0.0802   0.6939   0.9340
   0.500   0.4778   0.01216   0.00559  -0.0802   0.6891   0.9379
   0.750   0.5050   0.01216   0.00553  -0.0802   0.6848   0.9417
   1.000   0.5313   0.01216   0.00544  -0.0801   0.6812   0.9458
   1.250   0.5608   0.01218   0.00543  -0.0807   0.6769   0.9482
   1.500   0.5892   0.01221   0.00544  -0.0810   0.6717   0.9512
   1.750   0.6181   0.01221   0.00539  -0.0815   0.6674   0.9543
   2.000   0.6462   0.01223   0.00535  -0.0817   0.6632   0.9575
   2.250   0.6730   0.01227   0.00543  -0.0818   0.6573   0.9609
   2.500   0.7042   0.01229   0.00541  -0.0827   0.6522   0.9634
   2.750   0.7346   0.01232   0.00541  -0.0835   0.6474   0.9662
   3.000   0.7618   0.01237   0.00550  -0.0837   0.6408   0.9699
   3.250   0.7915   0.01239   0.00549  -0.0844   0.6355   0.9729
   3.500   0.8221   0.01246   0.00559  -0.0853   0.6289   0.9757
   3.750   0.8528   0.01250   0.00565  -0.0862   0.6224   0.9791
   4.000   0.8823   0.01256   0.00571  -0.0869   0.6157   0.9832
   4.250   0.9134   0.01263   0.00582  -0.0880   0.6078   0.9864
   4.500   0.9441   0.01270   0.00592  -0.0889   0.6000   0.9901
   4.750   0.9739   0.01277   0.00600  -0.0897   0.5913   0.9948
   5.000   0.9995   0.01287   0.00616  -0.0897   0.5820   1.0000
   5.250   1.0151   0.01295   0.00622  -0.0875   0.5736   1.0000
   5.500   1.0313   0.01308   0.00639  -0.0855   0.5635   1.0000
   5.750   1.0508   0.01322   0.00656  -0.0842   0.5530   1.0000
   6.000   1.0716   0.01337   0.00671  -0.0831   0.5417   1.0000
   6.250   1.0924   0.01356   0.00689  -0.0821   0.5292   1.0000
   6.500   1.1124   0.01377   0.00711  -0.0809   0.5152   1.0000
   6.750   1.1317   0.01403   0.00737  -0.0797   0.4999   1.0000
   7.000   1.1499   0.01432   0.00764  -0.0782   0.4833   1.0000
   7.250   1.1667   0.01465   0.00796  -0.0765   0.4653   1.0000
   7.500   1.1811   0.01503   0.00832  -0.0744   0.4466   1.0000
   7.750   1.1929   0.01548   0.00871  -0.0719   0.4273   1.0000
   8.000   1.2034   0.01602   0.00919  -0.0692   0.4072   1.0000
   8.250   1.2132   0.01663   0.00976  -0.0666   0.3862   1.0000
   8.500   1.2214   0.01735   0.01042  -0.0639   0.3656   1.0000
   8.750   1.2294   0.01813   0.01115  -0.0613   0.3453   1.0000
   9.000   1.2370   0.01899   0.01197  -0.0588   0.3255   1.0000
   9.250   1.2433   0.01997   0.01289  -0.0562   0.3061   1.0000
   9.500   1.2498   0.02101   0.01389  -0.0539   0.2880   1.0000
   9.750   1.2565   0.02211   0.01497  -0.0518   0.2693   1.0000
  10.000   1.2625   0.02331   0.01614  -0.0497   0.2512   1.0000
  10.250   1.2674   0.02464   0.01743  -0.0476   0.2329   1.0000
  10.500   1.2722   0.02604   0.01879  -0.0457   0.2158   1.0000
  10.750   1.2776   0.02747   0.02020  -0.0440   0.1990   1.0000
  11.000   1.2830   0.02896   0.02167  -0.0424   0.1831   1.0000
  11.250   1.2881   0.03051   0.02322  -0.0408   0.1680   1.0000
  11.500   1.2931   0.03213   0.02483  -0.0394   0.1539   1.0000
  11.750   1.2978   0.03383   0.02651  -0.0381   0.1403   1.0000
  12.000   1.3022   0.03559   0.02827  -0.0368   0.1277   1.0000
  12.250   1.3062   0.03745   0.03013  -0.0356   0.1155   1.0000
  12.500   1.3098   0.03939   0.03207  -0.0345   0.1047   1.0000
  12.750   1.3139   0.04134   0.03406  -0.0336   0.0944   1.0000
  13.000   1.3182   0.04335   0.03610  -0.0327   0.0849   1.0000
  13.250   1.3215   0.04550   0.03829  -0.0319   0.0766   1.0000
  13.500   1.3235   0.04785   0.04066  -0.0312   0.0694   1.0000
  13.750   1.3273   0.05008   0.04296  -0.0307   0.0622   1.0000
  14.000   1.3295   0.05255   0.04548  -0.0302   0.0566   1.0000
  14.250   1.3313   0.05512   0.04811  -0.0298   0.0511   1.0000
  14.500   1.3331   0.05777   0.05086  -0.0295   0.0464   1.0000
  14.750   1.3332   0.06068   0.05382  -0.0294   0.0421   1.0000
  15.000   1.3341   0.06359   0.05684  -0.0294   0.0385   1.0000
  15.250   1.3340   0.06668   0.06001  -0.0295   0.0353   1.0000
  15.500   1.3321   0.07009   0.06350  -0.0297   0.0326   1.0000
  15.750   1.3324   0.07330   0.06684  -0.0301   0.0300   1.0000
  16.000   1.3294   0.07704   0.07066  -0.0307   0.0279   1.0000
  16.250   1.3272   0.08076   0.07449  -0.0314   0.0260   1.0000
  16.500   1.3254   0.08449   0.07836  -0.0322   0.0241   1.0000
  16.750   1.3209   0.08869   0.08266  -0.0332   0.0227   1.0000
  17.000   1.3156   0.09313   0.08722  -0.0345   0.0214   1.0000
  17.250   1.3129   0.09725   0.09149  -0.0357   0.0200   1.0000
  17.500   1.3086   0.10168   0.09606  -0.0373   0.0188   1.0000
  17.750   1.3014   0.10668   0.10115  -0.0392   0.0179   1.0000
  18.000   1.2958   0.11150   0.10611  -0.0410   0.0170   1.0000
  18.250   1.2916   0.11616   0.11092  -0.0430   0.0159   1.0000
  18.500   1.2859   0.12113   0.11603  -0.0452   0.0152   1.0000
  18.750   1.2792   0.12637   0.12138  -0.0477   0.0144   1.0000
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