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EPPLER 598 AIRFOIL (e598-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 598 AIRFOIL (e598-il)
Reynolds number: 50,000
Max Cl/Cd: 23.49 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e598-il-50000-n5.txt
Download as CSV file: xf-e598-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 598 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3590   0.13110   0.12488  -0.0013   1.0000   0.0864
 -10.250  -0.3578   0.12866   0.12252  -0.0042   1.0000   0.0875
 -10.000  -0.3562   0.12599   0.11995  -0.0070   1.0000   0.0880
  -9.750  -0.3525   0.12286   0.11691  -0.0097   1.0000   0.0881
  -9.500  -0.3469   0.11947   0.11361  -0.0120   1.0000   0.0882
  -9.250  -0.3410   0.11589   0.11011  -0.0145   1.0000   0.0883
  -9.000  -0.3313   0.11195   0.10626  -0.0164   1.0000   0.0881
  -8.750  -0.3129   0.10351   0.09779  -0.0175   1.0000   0.0551
  -8.500  -0.3048   0.09981   0.09419  -0.0199   1.0000   0.0542
  -8.250  -0.2963   0.09609   0.09057  -0.0233   0.9439   0.0532
  -8.000  -0.2826   0.09168   0.08609  -0.0284   0.8935   0.0523
  -7.500  -0.2841   0.08303   0.07732  -0.0372   0.8417   0.0485
  -7.250  -0.2799   0.07931   0.07352  -0.0399   0.8245   0.0484
  -7.000  -0.2740   0.07568   0.06981  -0.0421   0.8102   0.0482
  -6.750  -0.2674   0.07181   0.06585  -0.0446   0.7978   0.0479
  -6.500  -0.2589   0.06770   0.06164  -0.0474   0.7860   0.0476
  -6.250  -0.2495   0.06332   0.05712  -0.0502   0.7759   0.0474
  -6.000  -0.2389   0.05862   0.05221  -0.0530   0.7666   0.0474
  -5.750  -0.2267   0.05314   0.04639  -0.0562   0.7576   0.0481
  -5.500  -0.2109   0.05042   0.04347  -0.0567   0.7492   0.0504
  -5.250  -0.1931   0.04691   0.03963  -0.0580   0.7403   0.0530
  -5.000  -0.1753   0.04230   0.03439  -0.0590   0.7334   0.0550
  -4.750  -0.1542   0.03962   0.03134  -0.0593   0.7251   0.0590
  -4.500  -0.1321   0.03674   0.02785  -0.0592   0.7179   0.0644
  -4.250  -0.1086   0.03510   0.02594  -0.0591   0.7102   0.0709
  -4.000  -0.0840   0.03308   0.02340  -0.0588   0.7031   0.0789
  -3.750  -0.0584   0.03150   0.02132  -0.0582   0.6967   0.0889
  -3.500  -0.0327   0.03053   0.02017  -0.0581   0.6889   0.0994
  -3.250  -0.0071   0.02955   0.01897  -0.0574   0.6830   0.1107
  -3.000   0.0198   0.02871   0.01792  -0.0574   0.6757   0.1232
  -2.750   0.0468   0.02794   0.01693  -0.0570   0.6694   0.1368
  -2.500   0.0744   0.02728   0.01606  -0.0566   0.6636   0.1516
  -2.250   0.1030   0.02680   0.01545  -0.0568   0.6564   0.1679
  -2.000   0.1310   0.02632   0.01484  -0.0565   0.6510   0.1862
  -1.750   0.1585   0.02599   0.01445  -0.0565   0.6447   0.2073
  -1.500   0.1855   0.02569   0.01409  -0.0563   0.6382   0.2326
  -1.250   0.2116   0.02530   0.01369  -0.0557   0.6334   0.2649
  -1.000   0.2368   0.02499   0.01361  -0.0557   0.6269   0.3109
  -0.500   0.3226   0.02273   0.01297  -0.0599   0.6160   1.0000
  -0.250   0.3474   0.02325   0.01323  -0.0599   0.6090   1.0000
   0.000   0.3720   0.02362   0.01331  -0.0593   0.6034   1.0000
   0.250   0.3969   0.02387   0.01326  -0.0584   0.5991   1.0000
   0.500   0.4207   0.02451   0.01377  -0.0584   0.5919   1.0000
   0.750   0.4451   0.02491   0.01397  -0.0579   0.5865   1.0000
   1.000   0.4701   0.02517   0.01401  -0.0570   0.5825   1.0000
   1.250   0.4929   0.02595   0.01472  -0.0570   0.5749   1.0000
   1.500   0.5172   0.02638   0.01501  -0.0565   0.5697   1.0000
   1.750   0.5424   0.02664   0.01509  -0.0556   0.5659   1.0000
   2.000   0.5639   0.02758   0.01603  -0.0557   0.5580   1.0000
   2.250   0.5880   0.02803   0.01638  -0.0550   0.5529   1.0000
   2.500   0.6134   0.02829   0.01650  -0.0542   0.5492   1.0000
   2.750   0.6330   0.02943   0.01769  -0.0543   0.5409   1.0000
   3.000   0.6572   0.02986   0.01805  -0.0536   0.5360   1.0000
   3.250   0.6809   0.03038   0.01852  -0.0530   0.5313   1.0000
   3.500   0.6998   0.03151   0.01970  -0.0528   0.5235   1.0000
   3.750   0.7244   0.03187   0.02000  -0.0521   0.5189   1.0000
   4.000   0.7440   0.03288   0.02104  -0.0517   0.5125   1.0000
   4.250   0.7638   0.03381   0.02202  -0.0512   0.5058   1.0000
   4.500   0.7896   0.03404   0.02221  -0.0504   0.5018   1.0000
   4.750   0.8028   0.03571   0.02398  -0.0502   0.4934   1.0000
   5.000   0.8251   0.03630   0.02458  -0.0495   0.4880   1.0000
   5.250   0.8528   0.03631   0.02459  -0.0486   0.4845   1.0000
   5.500   0.8583   0.03869   0.02712  -0.0483   0.4744   1.0000
   5.750   0.8841   0.03887   0.02731  -0.0475   0.4702   1.0000
   6.250   0.9115   0.04169   0.03032  -0.0462   0.4557   1.0000
   6.500   0.9388   0.04170   0.03036  -0.0453   0.4519   1.0000
   6.750   0.9345   0.04479   0.03359  -0.0447   0.4409   1.0000
   7.000   0.9647   0.04447   0.03332  -0.0438   0.4376   1.0000
   7.250   0.9521   0.04828   0.03724  -0.0432   0.4257   1.0000
   7.500   0.9827   0.04785   0.03690  -0.0422   0.4224   1.0000
   8.000   0.9736   0.05374   0.04293  -0.0408   0.4038   1.0000
   8.500   0.9947   0.05673   0.04607  -0.0393   0.3901   1.0000
   9.000   0.9626   0.06616   0.05559  -0.0402   0.3666   1.0000
   9.250   0.9891   0.06581   0.05538  -0.0389   0.3624   1.0000
   9.750   1.0021   0.06997   0.05972  -0.0382   0.3469   1.0000
  10.250   1.0156   0.07409   0.06405  -0.0375   0.3314   1.0000
  10.500   0.9987   0.07943   0.06943  -0.0387   0.3195   1.0000
  10.750   1.0303   0.07806   0.06823  -0.0369   0.3160   1.0000
  11.000   1.0122   0.08371   0.07392  -0.0383   0.3037   1.0000
  11.500   1.0255   0.08804   0.07847  -0.0380   0.2881   1.0000
  12.000   1.0400   0.09215   0.08282  -0.0377   0.2725   1.0000
  12.500   1.0559   0.09592   0.08684  -0.0373   0.2571   1.0000
  12.750   1.0349   0.10295   0.09390  -0.0398   0.2452   1.0000
  13.250   1.0475   0.10749   0.09870  -0.0400   0.2296   1.0000
  13.750   1.0613   0.11172   0.10317  -0.0402   0.2143   1.0000
  14.250   1.0585   0.11946   0.11109  -0.0425   0.1975   1.0000
  15.250   1.0370   0.13973   0.13166  -0.0504   0.1644   1.0000
  15.500   1.0609   0.13796   0.13007  -0.0487   0.1588   1.0000
  16.000   1.0631   0.14556   0.13784  -0.0516   0.1451   1.0000
  16.500   1.0605   0.15473   0.14713  -0.0558   0.1319   1.0000
  16.750   1.0360   0.16598   0.15831  -0.0620   0.1245   1.0000
  17.000   1.0537   0.16553   0.15804  -0.0611   0.1195   1.0000
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