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EPPLER 598 AIRFOIL (e598-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 598 AIRFOIL (e598-il)
Reynolds number: 500,000
Max Cl/Cd: 109.33 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e598-il-500000.txt
Download as CSV file: xf-e598-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3213   0.08656   0.08334  -0.0133   0.6394   0.0213
  -7.750  -0.3327   0.08082   0.07763  -0.0180   0.6351   0.0220
  -7.500  -0.3440   0.07574   0.07257  -0.0223   0.6306   0.0221
  -6.750  -0.3903   0.03155   0.02736  -0.0459   0.6252   0.0124
  -6.500  -0.3775   0.02643   0.02171  -0.0462   0.6198   0.0119
  -6.250  -0.3614   0.02169   0.01616  -0.0457   0.6148   0.0112
  -6.000  -0.3392   0.01900   0.01291  -0.0450   0.6089   0.0109
  -5.750  -0.3143   0.01751   0.01110  -0.0445   0.6031   0.0109
  -5.500  -0.2886   0.01643   0.00977  -0.0440   0.5980   0.0110
  -5.250  -0.2622   0.01548   0.00867  -0.0436   0.5924   0.0113
  -5.000  -0.2356   0.01471   0.00774  -0.0432   0.5870   0.0116
  -4.750  -0.2088   0.01407   0.00692  -0.0428   0.5821   0.0123
  -4.500  -0.1819   0.01333   0.00611  -0.0424   0.5773   0.0130
  -4.250  -0.1545   0.01281   0.00553  -0.0421   0.5725   0.0144
  -4.000  -0.1272   0.01232   0.00494  -0.0418   0.5679   0.0166
  -3.750  -0.0996   0.01187   0.00444  -0.0415   0.5635   0.0219
  -3.500  -0.0720   0.01143   0.00404  -0.0413   0.5590   0.0329
  -3.250  -0.0440   0.01123   0.00385  -0.0412   0.5547   0.0437
  -3.000  -0.0161   0.01114   0.00373  -0.0410   0.5505   0.0534
  -2.750   0.0122   0.01103   0.00363  -0.0410   0.5464   0.0630
  -2.500   0.0404   0.01089   0.00351  -0.0409   0.5422   0.0727
  -2.250   0.0685   0.01074   0.00335  -0.0407   0.5382   0.0822
  -2.000   0.0965   0.01065   0.00319  -0.0406   0.5342   0.0915
  -1.750   0.1248   0.01056   0.00310  -0.0405   0.5303   0.1012
  -1.500   0.1529   0.01039   0.00297  -0.0404   0.5264   0.1131
  -1.250   0.1810   0.01026   0.00285  -0.0403   0.5225   0.1259
  -1.000   0.2090   0.01017   0.00274  -0.0402   0.5187   0.1400
  -0.750   0.2371   0.01009   0.00267  -0.0401   0.5150   0.1568
  -0.500   0.2653   0.00995   0.00261  -0.0400   0.5112   0.1785
  -0.250   0.2933   0.00980   0.00255  -0.0399   0.5072   0.2116
   0.000   0.3208   0.00962   0.00251  -0.0398   0.5035   0.2685
   0.250   0.3471   0.00929   0.00251  -0.0397   0.4998   0.3905
   0.500   0.3887   0.00770   0.00260  -0.0422   0.4958   0.9733
   0.750   0.4431   0.00772   0.00251  -0.0477   0.4910   1.0000
   1.000   0.4697   0.00780   0.00250  -0.0473   0.4873   1.0000
   1.250   0.4962   0.00792   0.00252  -0.0469   0.4836   1.0000
   1.500   0.5232   0.00796   0.00255  -0.0466   0.4797   1.0000
   1.750   0.5500   0.00802   0.00256  -0.0463   0.4756   1.0000
   2.000   0.5768   0.00810   0.00258  -0.0459   0.4718   1.0000
   2.250   0.6034   0.00824   0.00264  -0.0456   0.4678   1.0000
   2.500   0.6304   0.00829   0.00270  -0.0453   0.4639   1.0000
   2.750   0.6574   0.00836   0.00274  -0.0450   0.4597   1.0000
   3.000   0.6841   0.00845   0.00279  -0.0447   0.4556   1.0000
   3.250   0.7108   0.00859   0.00287  -0.0444   0.4516   1.0000
   3.500   0.7379   0.00865   0.00295  -0.0442   0.4472   1.0000
   3.750   0.7648   0.00873   0.00302  -0.0439   0.4428   1.0000
   4.000   0.7915   0.00885   0.00310  -0.0437   0.4386   1.0000
   4.250   0.8184   0.00896   0.00321  -0.0434   0.4341   1.0000
   4.500   0.8454   0.00904   0.00331  -0.0432   0.4292   1.0000
   4.750   0.8722   0.00915   0.00340  -0.0430   0.4246   1.0000
   5.000   0.8989   0.00930   0.00353  -0.0428   0.4199   1.0000
   5.250   0.9259   0.00939   0.00366  -0.0426   0.4148   1.0000
   5.500   0.9527   0.00950   0.00377  -0.0424   0.4096   1.0000
   5.750   0.9793   0.00967   0.00392  -0.0422   0.4046   1.0000
   6.000   1.0063   0.00976   0.00407  -0.0421   0.3988   1.0000
   6.250   1.0328   0.00991   0.00421  -0.0419   0.3930   1.0000
   6.500   1.0594   0.01006   0.00439  -0.0417   0.3870   1.0000
   6.750   1.0859   0.01020   0.00454  -0.0416   0.3803   1.0000
   7.000   1.1121   0.01039   0.00474  -0.0414   0.3739   1.0000
   7.250   1.1386   0.01053   0.00493  -0.0412   0.3666   1.0000
   7.500   1.1644   0.01076   0.00513  -0.0410   0.3597   1.0000
   7.750   1.1907   0.01091   0.00536  -0.0409   0.3519   1.0000
   8.000   1.2161   0.01116   0.00560  -0.0406   0.3444   1.0000
   8.250   1.2420   0.01136   0.00585  -0.0405   0.3358   1.0000
   8.500   1.2672   0.01162   0.00613  -0.0402   0.3272   1.0000
   8.750   1.2921   0.01190   0.00642  -0.0399   0.3177   1.0000
   9.000   1.3171   0.01216   0.00673  -0.0397   0.3081   1.0000
   9.250   1.3412   0.01251   0.00708  -0.0394   0.2979   1.0000
   9.500   1.3645   0.01290   0.00746  -0.0390   0.2863   1.0000
   9.750   1.3881   0.01327   0.00786  -0.0386   0.2742   1.0000
  10.000   1.4106   0.01370   0.00831  -0.0381   0.2611   1.0000
  10.250   1.4319   0.01423   0.00882  -0.0376   0.2464   1.0000
  10.500   1.4521   0.01481   0.00939  -0.0369   0.2314   1.0000
  10.750   1.4708   0.01548   0.01004  -0.0361   0.2159   1.0000
  11.000   1.4873   0.01627   0.01078  -0.0350   0.1996   1.0000
  11.250   1.5021   0.01711   0.01159  -0.0338   0.1831   1.0000
  11.500   1.5137   0.01808   0.01251  -0.0323   0.1661   1.0000
  11.750   1.5207   0.01918   0.01358  -0.0302   0.1507   1.0000
  12.000   1.5195   0.02044   0.01482  -0.0272   0.1390   1.0000
  12.250   1.5159   0.02218   0.01657  -0.0251   0.1282   1.0000
  12.500   1.5123   0.02440   0.01878  -0.0238   0.1184   1.0000
  12.750   1.5116   0.02664   0.02105  -0.0232   0.1093   1.0000
  13.000   1.5086   0.02926   0.02369  -0.0227   0.1007   1.0000
  13.250   1.5034   0.03220   0.02664  -0.0224   0.0936   1.0000
  13.500   1.4999   0.03503   0.02951  -0.0221   0.0864   1.0000
  13.750   1.4945   0.03811   0.03262  -0.0220   0.0804   1.0000
  14.000   1.4881   0.04135   0.03589  -0.0220   0.0745   1.0000
  14.250   1.4826   0.04454   0.03913  -0.0220   0.0695   1.0000
  14.500   1.4746   0.04806   0.04267  -0.0222   0.0645   1.0000
  14.750   1.4680   0.05148   0.04615  -0.0224   0.0603   1.0000
  15.000   1.4610   0.05513   0.04984  -0.0229   0.0560   1.0000
  15.250   1.4545   0.05886   0.05361  -0.0235   0.0522   1.0000
  15.500   1.4484   0.06266   0.05746  -0.0243   0.0484   1.0000
  15.750   1.4405   0.06679   0.06163  -0.0252   0.0451   1.0000
  16.000   1.4362   0.07055   0.06546  -0.0261   0.0420   1.0000
  16.250   1.4269   0.07509   0.07004  -0.0273   0.0395   1.0000
  16.500   1.4240   0.07881   0.07384  -0.0284   0.0366   1.0000
  16.750   1.4168   0.08324   0.07831  -0.0297   0.0341   1.0000
  17.000   1.4093   0.08783   0.08298  -0.0312   0.0323   1.0000
  17.250   1.4057   0.09186   0.08708  -0.0326   0.0299   1.0000
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