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EPPLER 434 AIRFOIL (e434-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 434 AIRFOIL (e434-il)
Reynolds number: 100,000
Max Cl/Cd: 50.73 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e434-il-100000-n5.txt
Download as CSV file: xf-e434-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1451   0.11734   0.11277  -0.0698   0.9623   0.0445
 -11.250  -0.1418   0.11364   0.10906  -0.0735   0.9584   0.0447
 -11.000  -0.1391   0.10986   0.10529  -0.0765   0.9519   0.0449
 -10.750  -0.1349   0.10568   0.10111  -0.0800   0.9469   0.0450
 -10.500  -0.1280   0.10134   0.09677  -0.0832   0.9423   0.0451
 -10.250  -0.1128   0.09674   0.09215  -0.0835   0.9362   0.0456
 -10.000  -0.1031   0.09243   0.08783  -0.0859   0.9314   0.0458
  -9.750  -0.0981   0.08799   0.08338  -0.0889   0.9259   0.0457
  -9.000  -0.1746   0.08521   0.08041  -0.0900   0.9334   0.0248
  -8.750  -0.1559   0.08228   0.07743  -0.0919   0.9285   0.0235
  -8.250  -0.1527   0.06974   0.06485  -0.1050   0.9069   0.0200
  -8.000  -0.1490   0.06561   0.06067  -0.1088   0.8980   0.0197
  -7.750  -0.1516   0.06242   0.05740  -0.1100   0.8871   0.0193
  -7.500  -0.1520   0.05841   0.05327  -0.1117   0.8787   0.0190
  -7.250  -0.1522   0.05468   0.04938  -0.1124   0.8700   0.0187
  -7.000  -0.1498   0.05107   0.04557  -0.1125   0.8628   0.0181
  -6.750  -0.1479   0.04729   0.04153  -0.1118   0.8552   0.0177
  -6.500  -0.1412   0.04319   0.03705  -0.1113   0.8498   0.0172
  -6.250  -0.1356   0.04019   0.03372  -0.1094   0.8423   0.0172
  -6.000  -0.1213   0.03764   0.03080  -0.1086   0.8374   0.0179
  -5.750  -0.1072   0.03498   0.02770  -0.1073   0.8323   0.0186
  -5.500  -0.0928   0.03256   0.02477  -0.1055   0.8263   0.0193
  -5.250  -0.0724   0.03007   0.02166  -0.1044   0.8221   0.0202
  -5.000  -0.0486   0.02838   0.01969  -0.1040   0.8186   0.0207
  -4.750  -0.0298   0.02705   0.01813  -0.1025   0.8127   0.0214
  -4.500  -0.0055   0.02567   0.01649  -0.1018   0.8085   0.0221
  -4.250   0.0216   0.02429   0.01485  -0.1014   0.8052   0.0232
  -4.000   0.0449   0.02324   0.01359  -0.1004   0.8009   0.0248
  -3.750   0.0658   0.02264   0.01300  -0.0994   0.7957   0.0278
  -3.500   0.0902   0.02187   0.01214  -0.0988   0.7918   0.0320
  -3.250   0.1166   0.02112   0.01124  -0.0984   0.7888   0.0369
  -3.000   0.1356   0.02065   0.01082  -0.0970   0.7835   0.0464
  -2.750   0.1570   0.02004   0.01029  -0.0959   0.7788   0.0690
  -2.500   0.1806   0.01919   0.00982  -0.0953   0.7753   0.1453
  -2.250   0.2011   0.01790   0.00948  -0.0945   0.7725   0.3753
  -2.000   0.2027   0.01728   0.01028  -0.0882   0.7662   0.7105
  -1.750   0.2185   0.01759   0.01057  -0.0844   0.7619   0.8228
  -1.500   0.2402   0.01781   0.01063  -0.0819   0.7587   0.8695
  -1.250   0.2638   0.01804   0.01070  -0.0800   0.7550   0.9021
  -1.000   0.2981   0.01833   0.01084  -0.0805   0.7502   0.9317
  -0.750   0.4095   0.01828   0.01043  -0.0961   0.7496   0.9656
  -0.500   0.4542   0.01822   0.01019  -0.0997   0.7461   0.9745
  -0.250   0.4933   0.01811   0.00991  -0.1022   0.7430   0.9796
   0.000   0.5243   0.01818   0.00988  -0.1034   0.7384   0.9848
   0.250   0.5556   0.01827   0.00990  -0.1047   0.7331   0.9894
   0.500   0.5880   0.01824   0.00977  -0.1060   0.7291   0.9935
   0.750   0.6226   0.01814   0.00957  -0.1076   0.7260   0.9967
   1.000   0.6425   0.01845   0.00988  -0.1069   0.7192   1.0000
   1.250   0.6612   0.01855   0.00993  -0.1055   0.7143   1.0000
   1.500   0.6852   0.01851   0.00982  -0.1048   0.7108   1.0000
   1.750   0.6914   0.01892   0.01027  -0.1014   0.7033   1.0000
   2.000   0.7104   0.01899   0.01031  -0.0999   0.6984   1.0000
   2.250   0.7358   0.01892   0.01017  -0.0994   0.6949   1.0000
   2.500   0.7363   0.01940   0.01072  -0.0949   0.6865   1.0000
   2.750   0.7578   0.01939   0.01067  -0.0938   0.6819   1.0000
   3.000   0.7681   0.01963   0.01093  -0.0908   0.6755   1.0000
   3.250   0.7799   0.01980   0.01111  -0.0881   0.6690   1.0000
   3.500   0.8066   0.01967   0.01096  -0.0878   0.6649   1.0000
   3.750   0.8066   0.02013   0.01147  -0.0831   0.6562   1.0000
   4.000   0.8321   0.02004   0.01137  -0.0827   0.6512   1.0000
   4.250   0.8442   0.02035   0.01171  -0.0801   0.6436   1.0000
   4.500   0.8676   0.02036   0.01177  -0.0794   0.6373   1.0000
   4.750   0.8881   0.02048   0.01192  -0.0783   0.6304   1.0000
   5.000   0.9088   0.02060   0.01208  -0.0772   0.6228   1.0000
   5.250   0.9314   0.02068   0.01219  -0.0763   0.6155   1.0000
   5.500   0.9527   0.02077   0.01236  -0.0753   0.6073   1.0000
   5.750   0.9719   0.02095   0.01259  -0.0740   0.5985   1.0000
   6.000   0.9992   0.02084   0.01253  -0.0738   0.5906   1.0000
   6.250   1.0134   0.02117   0.01295  -0.0718   0.5800   1.0000
   6.500   1.0366   0.02120   0.01304  -0.0710   0.5705   1.0000
   6.750   1.0601   0.02121   0.01310  -0.0703   0.5603   1.0000
   7.000   1.0734   0.02152   0.01349  -0.0680   0.5482   1.0000
   7.250   1.0898   0.02175   0.01380  -0.0662   0.5359   1.0000
   7.500   1.1078   0.02196   0.01406  -0.0647   0.5231   1.0000
   7.750   1.1252   0.02219   0.01435  -0.0631   0.5092   1.0000
   8.000   1.1414   0.02250   0.01471  -0.0614   0.4941   1.0000
   8.250   1.1564   0.02288   0.01513  -0.0596   0.4779   1.0000
   8.500   1.1709   0.02332   0.01560  -0.0578   0.4607   1.0000
   8.750   1.1849   0.02382   0.01610  -0.0560   0.4426   1.0000
   9.000   1.1983   0.02439   0.01667  -0.0541   0.4238   1.0000
   9.250   1.2078   0.02519   0.01748  -0.0520   0.4040   1.0000
   9.500   1.2170   0.02605   0.01832  -0.0499   0.3835   1.0000
   9.750   1.2259   0.02700   0.01922  -0.0479   0.3637   1.0000
  10.000   1.2323   0.02814   0.02036  -0.0458   0.3433   1.0000
  10.250   1.2384   0.02936   0.02158  -0.0438   0.3235   1.0000
  10.500   1.2438   0.03069   0.02286  -0.0419   0.3045   1.0000
  10.750   1.2487   0.03212   0.02430  -0.0401   0.2857   1.0000
  11.000   1.2529   0.03366   0.02584  -0.0383   0.2673   1.0000
  11.250   1.2565   0.03531   0.02748  -0.0367   0.2497   1.0000
  11.500   1.2591   0.03708   0.02925  -0.0351   0.2326   1.0000
  11.750   1.2615   0.03894   0.03111  -0.0336   0.2164   1.0000
  12.000   1.2632   0.04092   0.03309  -0.0323   0.2006   1.0000
  12.250   1.2650   0.04298   0.03517  -0.0311   0.1854   1.0000
  12.500   1.2664   0.04516   0.03737  -0.0300   0.1709   1.0000
  12.750   1.2671   0.04746   0.03969  -0.0290   0.1574   1.0000
  13.000   1.2673   0.04991   0.04215  -0.0282   0.1448   1.0000
  13.250   1.2681   0.05241   0.04472  -0.0275   0.1327   1.0000
  13.500   1.2685   0.05502   0.04739  -0.0270   0.1213   1.0000
  13.750   1.2685   0.05775   0.05018  -0.0265   0.1112   1.0000
  14.000   1.2674   0.06070   0.05317  -0.0262   0.1022   1.0000
  14.250   1.2654   0.06384   0.05636  -0.0261   0.0939   1.0000
  14.500   1.2650   0.06690   0.05953  -0.0260   0.0858   1.0000
  14.750   1.2616   0.07040   0.06305  -0.0262   0.0795   1.0000
  15.000   1.2604   0.07375   0.06654  -0.0264   0.0729   1.0000
  15.250   1.2567   0.07747   0.07031  -0.0269   0.0678   1.0000
  15.500   1.2547   0.08109   0.07409  -0.0274   0.0624   1.0000
  15.750   1.2493   0.08521   0.07822  -0.0282   0.0587   1.0000
  16.000   1.2482   0.08889   0.08209  -0.0289   0.0542   1.0000
  16.250   1.2438   0.09310   0.08639  -0.0300   0.0509   1.0000
  16.500   1.2404   0.09717   0.09056  -0.0311   0.0478   1.0000
  16.750   1.2378   0.10125   0.09480  -0.0323   0.0446   1.0000
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