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EPPLER 598 AIRFOIL (e598-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 598 AIRFOIL (e598-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.35 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e598-il-1000000-n5.txt
Download as CSV file: xf-e598-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.6226   0.05185   0.04882  -0.0340   0.5902   0.0038
  -9.250  -0.6679   0.02760   0.02362  -0.0454   0.5914   0.0037
  -9.000  -0.6508   0.02473   0.02042  -0.0455   0.5851   0.0037
  -8.750  -0.6308   0.02264   0.01805  -0.0454   0.5798   0.0037
  -8.500  -0.6093   0.02094   0.01610  -0.0451   0.5739   0.0037
  -8.250  -0.5863   0.01959   0.01452  -0.0448   0.5677   0.0037
  -8.000  -0.5624   0.01841   0.01315  -0.0444   0.5624   0.0037
  -7.750  -0.5377   0.01741   0.01196  -0.0441   0.5569   0.0037
  -7.500  -0.5125   0.01652   0.01090  -0.0437   0.5518   0.0038
  -7.250  -0.4869   0.01572   0.00995  -0.0434   0.5473   0.0038
  -7.000  -0.4608   0.01501   0.00911  -0.0431   0.5425   0.0038
  -6.750  -0.4344   0.01438   0.00834  -0.0428   0.5374   0.0038
  -6.500  -0.4077   0.01382   0.00765  -0.0425   0.5328   0.0038
  -6.250  -0.3808   0.01325   0.00699  -0.0423   0.5292   0.0039
  -6.000  -0.3540   0.01266   0.00628  -0.0420   0.5249   0.0039
  -5.750  -0.3268   0.01214   0.00564  -0.0417   0.5204   0.0040
  -5.500  -0.2994   0.01172   0.00513  -0.0415   0.5162   0.0042
  -5.250  -0.2718   0.01133   0.00468  -0.0413   0.5130   0.0043
  -5.000  -0.2439   0.01102   0.00430  -0.0411   0.5093   0.0045
  -4.750  -0.2160   0.01074   0.00395  -0.0409   0.5052   0.0048
  -4.500  -0.1880   0.01050   0.00365  -0.0407   0.5012   0.0051
  -4.250  -0.1599   0.01026   0.00336  -0.0406   0.4981   0.0055
  -4.000  -0.1318   0.01001   0.00308  -0.0404   0.4949   0.0063
  -3.750  -0.1037   0.00980   0.00283  -0.0402   0.4912   0.0076
  -3.500  -0.0756   0.00960   0.00260  -0.0401   0.4873   0.0100
  -3.250  -0.0475   0.00940   0.00240  -0.0400   0.4840   0.0146
  -3.000  -0.0192   0.00921   0.00223  -0.0399   0.4812   0.0200
  -2.750   0.0091   0.00906   0.00208  -0.0398   0.4778   0.0258
  -2.500   0.0373   0.00892   0.00195  -0.0397   0.4741   0.0324
  -2.250   0.0656   0.00879   0.00184  -0.0396   0.4707   0.0419
  -2.000   0.0938   0.00865   0.00175  -0.0395   0.4675   0.0551
  -1.750   0.1223   0.00854   0.00167  -0.0395   0.4644   0.0644
  -1.500   0.1507   0.00845   0.00159  -0.0394   0.4609   0.0724
  -1.250   0.1792   0.00839   0.00152  -0.0394   0.4574   0.0800
  -1.000   0.2077   0.00834   0.00147  -0.0393   0.4538   0.0884
  -0.750   0.2362   0.00827   0.00142  -0.0393   0.4506   0.0989
  -0.500   0.2648   0.00821   0.00138  -0.0393   0.4474   0.1083
  -0.250   0.2933   0.00817   0.00135  -0.0393   0.4437   0.1181
   0.000   0.3218   0.00813   0.00132  -0.0393   0.4397   0.1299
   0.250   0.3502   0.00810   0.00130  -0.0393   0.4362   0.1441
   0.500   0.3788   0.00804   0.00129  -0.0393   0.4329   0.1610
   1.000   0.4355   0.00794   0.00130  -0.0393   0.4248   0.2110
   1.250   0.4637   0.00789   0.00132  -0.0393   0.4209   0.2463
   1.500   0.4919   0.00779   0.00134  -0.0393   0.4172   0.2956
   1.750   0.5195   0.00760   0.00137  -0.0393   0.4130   0.3854
   2.250   0.5894   0.00624   0.00155  -0.0423   0.4041   0.9935
   2.500   0.6311   0.00629   0.00156  -0.0452   0.3992   0.9991
   2.750   0.6609   0.00637   0.00160  -0.0456   0.3943   1.0000
   3.000   0.6878   0.00647   0.00166  -0.0453   0.3898   1.0000
   3.250   0.7148   0.00654   0.00171  -0.0451   0.3855   1.0000
   3.500   0.7417   0.00663   0.00178  -0.0448   0.3802   1.0000
   3.750   0.7685   0.00675   0.00185  -0.0445   0.3751   1.0000
   4.000   0.7955   0.00683   0.00193  -0.0443   0.3704   1.0000
   4.250   0.8223   0.00694   0.00202  -0.0441   0.3648   1.0000
   4.500   0.8491   0.00707   0.00212  -0.0439   0.3597   1.0000
   4.750   0.8760   0.00717   0.00222  -0.0436   0.3542   1.0000
   5.000   0.9027   0.00731   0.00233  -0.0434   0.3481   1.0000
   5.250   0.9294   0.00744   0.00244  -0.0432   0.3424   1.0000
   5.500   0.9561   0.00758   0.00257  -0.0430   0.3357   1.0000
   5.750   0.9827   0.00775   0.00271  -0.0428   0.3287   1.0000
   6.000   1.0093   0.00790   0.00285  -0.0426   0.3208   1.0000
   6.250   1.0357   0.00809   0.00302  -0.0425   0.3129   1.0000
   6.500   1.0621   0.00828   0.00319  -0.0423   0.3039   1.0000
   6.750   1.0884   0.00848   0.00337  -0.0421   0.2958   1.0000
   7.000   1.1145   0.00871   0.00358  -0.0419   0.2865   1.0000
   7.250   1.1407   0.00893   0.00378  -0.0418   0.2771   1.0000
   7.500   1.1665   0.00918   0.00401  -0.0416   0.2674   1.0000
   7.750   1.1919   0.00948   0.00427  -0.0414   0.2564   1.0000
   8.000   1.2173   0.00978   0.00453  -0.0412   0.2444   1.0000
   8.250   1.2424   0.01010   0.00482  -0.0410   0.2326   1.0000
   8.500   1.2671   0.01045   0.00514  -0.0407   0.2201   1.0000
   8.750   1.2911   0.01086   0.00550  -0.0404   0.2060   1.0000
   9.000   1.3145   0.01133   0.00590  -0.0400   0.1905   1.0000
   9.250   1.3375   0.01182   0.00634  -0.0396   0.1757   1.0000
   9.500   1.3590   0.01242   0.00685  -0.0391   0.1583   1.0000
   9.750   1.3800   0.01304   0.00739  -0.0385   0.1411   1.0000
  10.000   1.4007   0.01364   0.00794  -0.0378   0.1273   1.0000
  10.250   1.4204   0.01428   0.00853  -0.0371   0.1140   1.0000
  10.500   1.4394   0.01494   0.00915  -0.0363   0.1023   1.0000
  10.750   1.4569   0.01566   0.00982  -0.0353   0.0909   1.0000
  11.000   1.4722   0.01645   0.01057  -0.0341   0.0794   1.0000
  11.250   1.4863   0.01726   0.01135  -0.0328   0.0704   1.0000
  11.750   1.5006   0.01909   0.01316  -0.0282   0.0556   1.0000
  12.000   1.5019   0.02030   0.01439  -0.0259   0.0508   1.0000
  12.250   1.5012   0.02205   0.01615  -0.0243   0.0452   1.0000
  12.500   1.4994   0.02425   0.01836  -0.0233   0.0381   1.0000
  12.750   1.4980   0.02666   0.02077  -0.0228   0.0324   1.0000
  13.000   1.5034   0.02855   0.02272  -0.0225   0.0309   1.0000
  13.250   1.5023   0.03111   0.02531  -0.0222   0.0272   1.0000
  13.500   1.5073   0.03311   0.02738  -0.0220   0.0270   1.0000
  13.750   1.5024   0.03612   0.03043  -0.0219   0.0230   1.0000
  14.000   1.5028   0.03864   0.03300  -0.0218   0.0215   1.0000
  14.500   1.4960   0.04456   0.03901  -0.0218   0.0174   1.0000
  14.750   1.4935   0.04749   0.04201  -0.0219   0.0164   1.0000
  15.000   1.4908   0.05049   0.04507  -0.0221   0.0152   1.0000
  15.250   1.4865   0.05382   0.04845  -0.0226   0.0137   1.0000
  15.500   1.4845   0.05700   0.05170  -0.0230   0.0130   1.0000
  15.750   1.4829   0.06018   0.05494  -0.0236   0.0123   1.0000
  16.000   1.4803   0.06356   0.05839  -0.0243   0.0114   1.0000
  16.250   1.4776   0.06701   0.06190  -0.0250   0.0108   1.0000
  16.500   1.4744   0.07063   0.06560  -0.0259   0.0099   1.0000
  16.750   1.4708   0.07437   0.06940  -0.0269   0.0090   1.0000
  17.000   1.4675   0.07812   0.07321  -0.0279   0.0085   1.0000
  17.250   1.4635   0.08205   0.07721  -0.0291   0.0077   1.0000
  17.500   1.4590   0.08614   0.08138  -0.0304   0.0071   1.0000
  17.750   1.4556   0.09012   0.08542  -0.0317   0.0068   1.0000
  18.000   1.4516   0.09426   0.08964  -0.0332   0.0065   1.0000
  18.250   1.4468   0.09859   0.09405  -0.0348   0.0059   1.0000
  18.500   1.4431   0.10282   0.09836  -0.0364   0.0056   1.0000
  18.750   1.4371   0.10748   0.10309  -0.0383   0.0052   1.0000
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