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EPPLER 598 AIRFOIL (e598-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 598 AIRFOIL (e598-il)
Reynolds number: 500,000
Max Cl/Cd: 106.3 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e598-il-500000-n5.txt
Download as CSV file: xf-e598-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3599   0.09381   0.09031  -0.0076   0.6011   0.0070
  -8.750  -0.3590   0.08968   0.08618  -0.0096   0.5967   0.0068
  -8.250  -0.5565   0.02880   0.02427  -0.0454   0.6100   0.0053
  -8.000  -0.5398   0.02544   0.02044  -0.0456   0.6038   0.0053
  -7.750  -0.5194   0.02325   0.01788  -0.0455   0.5980   0.0054
  -7.500  -0.4972   0.02150   0.01582  -0.0452   0.5919   0.0054
  -7.250  -0.4738   0.02009   0.01413  -0.0448   0.5855   0.0055
  -7.000  -0.4494   0.01892   0.01272  -0.0445   0.5799   0.0055
  -6.750  -0.4243   0.01792   0.01151  -0.0441   0.5742   0.0056
  -6.500  -0.3986   0.01706   0.01046  -0.0438   0.5689   0.0056
  -6.250  -0.3729   0.01621   0.00942  -0.0434   0.5641   0.0058
  -6.000  -0.3468   0.01542   0.00849  -0.0431   0.5589   0.0059
  -5.750  -0.3202   0.01479   0.00773  -0.0429   0.5537   0.0061
  -5.500  -0.2933   0.01428   0.00709  -0.0426   0.5493   0.0064
  -5.250  -0.2660   0.01378   0.00650  -0.0424   0.5451   0.0067
  -5.000  -0.2386   0.01335   0.00596  -0.0421   0.5404   0.0071
  -4.750  -0.2111   0.01297   0.00545  -0.0419   0.5359   0.0077
  -4.500  -0.1836   0.01255   0.00496  -0.0416   0.5319   0.0085
  -4.250  -0.1558   0.01221   0.00454  -0.0414   0.5281   0.0097
  -4.000  -0.1281   0.01187   0.00416  -0.0412   0.5239   0.0117
  -3.750  -0.1004   0.01158   0.00382  -0.0410   0.5198   0.0153
  -3.500  -0.0726   0.01132   0.00354  -0.0409   0.5161   0.0210
  -3.250  -0.0447   0.01107   0.00332  -0.0407   0.5125   0.0291
  -3.000  -0.0168   0.01086   0.00313  -0.0406   0.5087   0.0382
  -2.750   0.0112   0.01071   0.00297  -0.0405   0.5047   0.0476
  -2.500   0.0393   0.01059   0.00283  -0.0404   0.5011   0.0565
  -2.250   0.0674   0.01044   0.00270  -0.0403   0.4979   0.0647
  -2.000   0.0957   0.01031   0.00257  -0.0402   0.4942   0.0725
  -1.750   0.1239   0.01021   0.00246  -0.0401   0.4904   0.0806
  -1.500   0.1521   0.01013   0.00236  -0.0400   0.4867   0.0894
  -1.250   0.1803   0.01005   0.00227  -0.0399   0.4836   0.0997
  -1.000   0.2086   0.00996   0.00220  -0.0398   0.4801   0.1101
  -0.750   0.2369   0.00988   0.00213  -0.0398   0.4762   0.1211
  -0.500   0.2652   0.00982   0.00207  -0.0397   0.4726   0.1333
  -0.250   0.2933   0.00978   0.00202  -0.0396   0.4692   0.1482
   0.000   0.3215   0.00970   0.00199  -0.0396   0.4658   0.1669
   0.250   0.3497   0.00961   0.00197  -0.0396   0.4620   0.1913
   0.500   0.3777   0.00952   0.00196  -0.0395   0.4583   0.2248
   0.750   0.4056   0.00942   0.00196  -0.0395   0.4546   0.2695
   1.000   0.4330   0.00925   0.00197  -0.0394   0.4511   0.3414
   1.500   0.5184   0.00764   0.00207  -0.0455   0.4425   0.9977
   1.750   0.5491   0.00772   0.00207  -0.0460   0.4385   1.0000
   2.000   0.5759   0.00780   0.00211  -0.0457   0.4349   1.0000
   2.250   0.6028   0.00787   0.00215  -0.0454   0.4306   1.0000
   2.500   0.6297   0.00795   0.00219  -0.0451   0.4263   1.0000
   2.750   0.6564   0.00806   0.00224  -0.0448   0.4223   1.0000
   3.000   0.6833   0.00814   0.00231  -0.0445   0.4182   1.0000
   3.250   0.7102   0.00823   0.00238  -0.0443   0.4136   1.0000
   3.500   0.7370   0.00834   0.00245  -0.0440   0.4090   1.0000
   3.750   0.7637   0.00845   0.00254  -0.0437   0.4047   1.0000
   4.000   0.7907   0.00855   0.00264  -0.0435   0.4000   1.0000
   4.250   0.8174   0.00867   0.00274  -0.0433   0.3949   1.0000
   4.500   0.8441   0.00881   0.00284  -0.0430   0.3901   1.0000
   4.750   0.8710   0.00892   0.00297  -0.0429   0.3850   1.0000
   5.000   0.8978   0.00905   0.00310  -0.0426   0.3795   1.0000
   5.250   0.9243   0.00921   0.00324  -0.0424   0.3745   1.0000
   5.500   0.9512   0.00934   0.00339  -0.0423   0.3688   1.0000
   5.750   0.9777   0.00951   0.00355  -0.0421   0.3627   1.0000
   6.000   1.0043   0.00967   0.00371  -0.0419   0.3569   1.0000
   6.250   1.0308   0.00984   0.00389  -0.0417   0.3500   1.0000
   6.500   1.0570   0.01004   0.00409  -0.0415   0.3432   1.0000
   6.750   1.0833   0.01023   0.00429  -0.0414   0.3352   1.0000
   7.000   1.1092   0.01045   0.00451  -0.0412   0.3275   1.0000
   7.250   1.1351   0.01068   0.00475  -0.0410   0.3187   1.0000
   7.500   1.1608   0.01092   0.00499  -0.0408   0.3105   1.0000
   7.750   1.1860   0.01122   0.00528  -0.0405   0.3012   1.0000
   8.000   1.2114   0.01148   0.00556  -0.0403   0.2917   1.0000
   8.250   1.2362   0.01180   0.00587  -0.0400   0.2816   1.0000
   8.500   1.2604   0.01217   0.00623  -0.0397   0.2705   1.0000
   8.750   1.2845   0.01254   0.00660  -0.0394   0.2584   1.0000
   9.000   1.3081   0.01294   0.00700  -0.0390   0.2464   1.0000
   9.250   1.3308   0.01340   0.00745  -0.0386   0.2332   1.0000
   9.500   1.3527   0.01393   0.00795  -0.0381   0.2186   1.0000
   9.750   1.3735   0.01452   0.00850  -0.0375   0.2036   1.0000
  10.000   1.3931   0.01518   0.00912  -0.0367   0.1879   1.0000
  10.250   1.4106   0.01597   0.00984  -0.0358   0.1710   1.0000
  10.500   1.4271   0.01677   0.01059  -0.0348   0.1546   1.0000
  10.750   1.4418   0.01762   0.01141  -0.0336   0.1401   1.0000
  11.000   1.4541   0.01855   0.01232  -0.0321   0.1270   1.0000
  11.250   1.4628   0.01957   0.01332  -0.0303   0.1157   1.0000
  11.500   1.4639   0.02073   0.01448  -0.0275   0.1067   1.0000
  11.750   1.4647   0.02220   0.01597  -0.0256   0.0984   1.0000
  12.000   1.4650   0.02406   0.01786  -0.0244   0.0911   1.0000
  12.250   1.4638   0.02633   0.02014  -0.0237   0.0831   1.0000
  12.500   1.4654   0.02851   0.02237  -0.0232   0.0767   1.0000
  12.750   1.4645   0.03102   0.02491  -0.0229   0.0713   1.0000
  13.000   1.4636   0.03358   0.02751  -0.0227   0.0655   1.0000
  13.250   1.4616   0.03632   0.03029  -0.0225   0.0611   1.0000
  13.500   1.4587   0.03917   0.03318  -0.0224   0.0562   1.0000
  13.750   1.4556   0.04208   0.03613  -0.0224   0.0528   1.0000
  14.000   1.4526   0.04503   0.03915  -0.0225   0.0490   1.0000
  14.500   1.4442   0.05133   0.04556  -0.0228   0.0426   1.0000
  14.750   1.4399   0.05466   0.04894  -0.0232   0.0399   1.0000
  15.000   1.4364   0.05801   0.05235  -0.0238   0.0374   1.0000
  15.250   1.4325   0.06152   0.05592  -0.0244   0.0346   1.0000
  15.500   1.4281   0.06518   0.05963  -0.0252   0.0323   1.0000
  15.750   1.4249   0.06874   0.06326  -0.0260   0.0299   1.0000
  16.000   1.4196   0.07268   0.06725  -0.0270   0.0278   1.0000
  16.250   1.4170   0.07635   0.07100  -0.0280   0.0261   1.0000
  16.500   1.4115   0.08049   0.07519  -0.0292   0.0240   1.0000
  16.750   1.4076   0.08446   0.07923  -0.0304   0.0222   1.0000
  17.000   1.4039   0.08852   0.08337  -0.0317   0.0209   1.0000
  17.250   1.3978   0.09294   0.08785  -0.0332   0.0192   1.0000
  17.500   1.3943   0.09706   0.09205  -0.0347   0.0179   1.0000
  17.750   1.3897   0.10145   0.09652  -0.0363   0.0169   1.0000
  18.000   1.3844   0.10601   0.10116  -0.0381   0.0163   1.0000
  18.250   1.3801   0.11040   0.10562  -0.0399   0.0146   1.0000
  18.500   1.3752   0.11501   0.11031  -0.0418   0.0138   1.0000
  18.750   1.3699   0.11975   0.11513  -0.0439   0.0130   1.0000
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