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EPPLER 598 AIRFOIL (e598-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 598 AIRFOIL (e598-il)
Reynolds number: 100,000
Max Cl/Cd: 43.26 at α=11.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e598-il-100000.txt
Download as CSV file: xf-e598-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2705   0.09633   0.09245  -0.0247   0.8950   0.0850
  -8.000  -0.2779   0.09474   0.09079  -0.0287   0.8657   0.0875
  -7.750  -0.2906   0.09328   0.08929  -0.0331   0.8451   0.0881
  -7.500  -0.2693   0.08801   0.08396  -0.0298   0.8317   0.0905
  -7.250  -0.2560   0.08516   0.08107  -0.0288   0.8180   0.0945
  -7.000  -0.2564   0.08279   0.07869  -0.0305   0.8058   0.0979
  -6.750  -0.2658   0.08074   0.07654  -0.0411   0.7953   0.1013
  -6.500  -0.2568   0.07611   0.07192  -0.0416   0.7856   0.1030
  -6.250  -0.2419   0.07303   0.06883  -0.0385   0.7767   0.1057
  -6.000  -0.2302   0.07011   0.06585  -0.0398   0.7680   0.1095
  -5.750  -0.2223   0.06633   0.06177  -0.0503   0.7607   0.1169
  -5.500  -0.2074   0.06261   0.05814  -0.0479   0.7528   0.1190
  -5.250  -0.1921   0.05974   0.05520  -0.0476   0.7460   0.1232
  -5.000  -0.1717   0.04374   0.03786  -0.0591   0.7425   0.0658
  -4.750  -0.1516   0.04368   0.03811  -0.0579   0.7346   0.0731
  -4.500  -0.1313   0.03866   0.03260  -0.0588   0.7288   0.0703
  -4.250  -0.1087   0.03418   0.02749  -0.0591   0.7222   0.0704
  -4.000  -0.0853   0.03086   0.02340  -0.0583   0.7169   0.0746
  -3.750  -0.0601   0.02929   0.02162  -0.0581   0.7099   0.0832
  -3.500  -0.0347   0.02783   0.01985  -0.0576   0.7033   0.0945
  -3.250  -0.0095   0.02663   0.01830  -0.0567   0.6984   0.1072
  -3.000   0.0181   0.02562   0.01705  -0.0568   0.6911   0.1205
  -2.750   0.0446   0.02476   0.01593  -0.0561   0.6852   0.1341
  -2.500   0.0714   0.02420   0.01516  -0.0557   0.6796   0.1485
  -2.250   0.0988   0.02367   0.01456  -0.0557   0.6729   0.1637
  -2.000   0.1252   0.02306   0.01387  -0.0551   0.6678   0.1798
  -1.750   0.1522   0.02268   0.01345  -0.0549   0.6619   0.1977
  -1.500   0.1789   0.02222   0.01310  -0.0548   0.6555   0.2178
  -1.250   0.2049   0.02181   0.01273  -0.0541   0.6508   0.2425
  -1.000   0.2310   0.02157   0.01264  -0.0539   0.6448   0.2743
  -0.750   0.2567   0.02117   0.01250  -0.0536   0.6386   0.3242
  -0.500   0.3282   0.01872   0.01180  -0.0605   0.6334   1.0000
  -0.250   0.3539   0.01926   0.01213  -0.0606   0.6269   1.0000
   0.000   0.3788   0.01962   0.01228  -0.0600   0.6210   1.0000
   0.250   0.4035   0.01985   0.01227  -0.0590   0.6167   1.0000
   0.500   0.4283   0.02051   0.01285  -0.0591   0.6101   1.0000
   0.750   0.4531   0.02091   0.01311  -0.0586   0.6042   1.0000
   1.000   0.4780   0.02112   0.01313  -0.0576   0.6001   1.0000
   1.250   0.5021   0.02190   0.01390  -0.0578   0.5932   1.0000
   1.500   0.5267   0.02234   0.01424  -0.0573   0.5874   1.0000
   1.750   0.5521   0.02251   0.01425  -0.0563   0.5835   1.0000
   2.000   0.5751   0.02346   0.01523  -0.0565   0.5761   1.0000
   2.250   0.5996   0.02391   0.01561  -0.0560   0.5706   1.0000
   2.500   0.6255   0.02402   0.01558  -0.0550   0.5669   1.0000
   2.750   0.6469   0.02519   0.01683  -0.0553   0.5588   1.0000
   3.000   0.6716   0.02558   0.01717  -0.0546   0.5535   1.0000
   3.250   0.6983   0.02561   0.01708  -0.0536   0.5501   1.0000
   3.500   0.7173   0.02708   0.01868  -0.0540   0.5411   1.0000
   3.750   0.7427   0.02732   0.01886  -0.0532   0.5364   1.0000
   4.000   0.7705   0.02723   0.01866  -0.0522   0.5333   1.0000
   4.250   0.7862   0.02905   0.02067  -0.0525   0.5233   1.0000
   4.500   0.8132   0.02905   0.02061  -0.0516   0.5192   1.0000
   4.750   0.8332   0.03015   0.02177  -0.0513   0.5124   1.0000
   5.000   0.8543   0.03099   0.02267  -0.0509   0.5054   1.0000
   5.250   0.8837   0.03067   0.02230  -0.0499   0.5021   1.0000
   5.500   0.8953   0.03281   0.02461  -0.0499   0.4923   1.0000
   5.750   0.9226   0.03273   0.02452  -0.0490   0.4878   1.0000
   6.000   0.9548   0.03209   0.02382  -0.0481   0.4850   1.0000
   6.250   0.9600   0.03482   0.02678  -0.0479   0.4737   1.0000
   6.500   0.9929   0.03404   0.02597  -0.0470   0.4704   1.0000
   6.750   0.9975   0.03673   0.02884  -0.0466   0.4600   1.0000
   7.000   1.0291   0.03605   0.02818  -0.0457   0.4559   1.0000
   7.250   1.0665   0.03478   0.02686  -0.0448   0.4532   1.0000
   7.500   1.0646   0.03792   0.03023  -0.0442   0.4414   1.0000
   7.750   1.1052   0.03622   0.02852  -0.0433   0.4386   1.0000
   8.000   1.1013   0.03941   0.03192  -0.0425   0.4272   1.0000
   8.250   1.1454   0.03727   0.02977  -0.0416   0.4240   1.0000
   8.500   1.1435   0.04003   0.03274  -0.0405   0.4135   1.0000
   8.750   1.1887   0.03773   0.03044  -0.0398   0.4094   1.0000
   9.000   1.2059   0.03836   0.03119  -0.0387   0.4016   1.0000
   9.250   1.2376   0.03739   0.03029  -0.0379   0.3947   1.0000
   9.500   1.2713   0.03629   0.02923  -0.0372   0.3881   1.0000
   9.750   1.2935   0.03618   0.02924  -0.0362   0.3792   1.0000
  10.000   1.3154   0.03613   0.02930  -0.0351   0.3705   1.0000
  10.250   1.3564   0.03424   0.02738  -0.0347   0.3622   1.0000
  10.500   1.3668   0.03506   0.02840  -0.0331   0.3513   1.0000
  10.750   1.3940   0.03438   0.02776  -0.0322   0.3409   1.0000
  11.000   1.4277   0.03319   0.02650  -0.0316   0.3296   1.0000
  11.250   1.4432   0.03336   0.02678  -0.0301   0.3170   1.0000
  11.500   1.4519   0.03399   0.02754  -0.0282   0.3042   1.0000
  11.750   1.4603   0.03458   0.02822  -0.0262   0.2912   1.0000
  12.000   1.4654   0.03531   0.02899  -0.0240   0.2784   1.0000
  12.250   1.4664   0.03622   0.02992  -0.0216   0.2660   1.0000
  12.500   1.4661   0.03741   0.03109  -0.0195   0.2534   1.0000
  12.750   1.4649   0.03891   0.03257  -0.0179   0.2406   1.0000
  13.000   1.4596   0.04094   0.03459  -0.0167   0.2282   1.0000
  13.250   1.4464   0.04402   0.03777  -0.0161   0.2169   1.0000
  13.500   1.4379   0.04692   0.04070  -0.0156   0.2051   1.0000
  13.750   1.4311   0.04979   0.04355  -0.0154   0.1935   1.0000
  14.000   1.4260   0.05262   0.04633  -0.0151   0.1818   1.0000
  14.250   1.4229   0.05529   0.04890  -0.0149   0.1703   1.0000
  14.500   1.4107   0.05922   0.05293  -0.0154   0.1608   1.0000
  14.750   1.4024   0.06285   0.05660  -0.0157   0.1513   1.0000
  15.000   1.3996   0.06582   0.05949  -0.0158   0.1415   1.0000
  15.250   1.3968   0.06886   0.06249  -0.0160   0.1322   1.0000
  15.500   1.3852   0.07339   0.06718  -0.0170   0.1251   1.0000
  15.750   1.3865   0.07611   0.06980  -0.0171   0.1163   1.0000
  16.000   1.3762   0.08067   0.07451  -0.0183   0.1102   1.0000
  16.250   1.3754   0.08394   0.07776  -0.0188   0.1031   1.0000
  16.500   1.3682   0.08827   0.08221  -0.0201   0.0975   1.0000
  16.750   1.3679   0.09163   0.08557  -0.0205   0.0916   1.0000
  17.000   1.3553   0.09705   0.09120  -0.0226   0.0876   1.0000
  17.250   1.0497   0.17311   0.16793  -0.0651   0.1154   1.0000
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