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EPPLER 555 AIRFOIL (e555-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 555 AIRFOIL (e555-il)
Reynolds number: 200,000
Max Cl/Cd: 69.12 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e555-il-200000.txt
Download as CSV file: xf-e555-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 555 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.5249   0.10167   0.09786  -0.0529   1.0000   0.0287
 -13.000  -0.5568   0.09118   0.08729  -0.0590   1.0000   0.0276
 -12.750  -0.6720   0.07221   0.06767  -0.0726   1.0000   0.0251
 -12.500  -0.6695   0.06888   0.06432  -0.0725   1.0000   0.0244
 -12.250  -0.6803   0.06491   0.06027  -0.0733   1.0000   0.0241
 -12.000  -0.6952   0.06080   0.05605  -0.0741   1.0000   0.0237
 -11.750  -0.7111   0.05698   0.05209  -0.0744   1.0000   0.0235
 -11.500  -0.7259   0.05358   0.04855  -0.0740   1.0000   0.0231
 -11.250  -0.7414   0.05045   0.04526  -0.0730   1.0000   0.0227
 -11.000  -0.7606   0.04754   0.04217  -0.0709   1.0000   0.0223
 -10.750  -0.7825   0.04536   0.03983  -0.0674   1.0000   0.0220
 -10.500  -0.8031   0.04293   0.03715  -0.0636   1.0000   0.0216
 -10.250  -0.8194   0.04035   0.03416  -0.0599   1.0000   0.0210
 -10.000  -0.8198   0.03845   0.03205  -0.0571   1.0000   0.0209
  -9.750  -0.8163   0.03668   0.03012  -0.0546   1.0000   0.0209
  -9.500  -0.8099   0.03503   0.02836  -0.0523   1.0000   0.0211
  -9.250  -0.8023   0.03358   0.02683  -0.0501   1.0000   0.0213
  -9.000  -0.7938   0.03229   0.02546  -0.0480   1.0000   0.0216
  -8.750  -0.7812   0.03107   0.02417  -0.0464   0.9996   0.0221
  -8.500  -0.7466   0.02953   0.02254  -0.0485   0.9958   0.0228
  -8.250  -0.7126   0.02816   0.02106  -0.0505   0.9916   0.0241
  -8.000  -0.6806   0.02663   0.01954  -0.0526   0.9865   0.0260
  -7.750  -0.6447   0.02558   0.01843  -0.0556   0.9818   0.0295
  -7.500  -0.6140   0.02395   0.01687  -0.0581   0.9754   0.0329
  -7.250  -0.5798   0.02226   0.01517  -0.0614   0.9701   0.0388
  -7.000  -0.5463   0.02074   0.01366  -0.0643   0.9635   0.0522
  -6.750  -0.5070   0.01837   0.01157  -0.0695   0.9598   0.0950
  -6.500  -0.4787   0.01521   0.00956  -0.0740   0.9524   0.2854
  -6.250  -0.4368   0.01508   0.00973  -0.0771   0.9479   0.4012
  -6.000  -0.3998   0.01546   0.00996  -0.0787   0.9417   0.4315
  -5.750  -0.3622   0.01581   0.01024  -0.0802   0.9357   0.4488
  -5.500  -0.3192   0.01610   0.01041  -0.0827   0.9324   0.4637
  -5.250  -0.2871   0.01651   0.01088  -0.0828   0.9250   0.4739
  -5.000  -0.2481   0.01671   0.01104  -0.0845   0.9203   0.4845
  -4.750  -0.2039   0.01677   0.01093  -0.0874   0.9175   0.4960
  -4.500  -0.1690   0.01725   0.01154  -0.0877   0.9116   0.5043
  -4.250  -0.1302   0.01720   0.01138  -0.0897   0.9058   0.5139
  -4.000  -0.0875   0.01701   0.01116  -0.0922   0.9021   0.5178
  -3.750  -0.0522   0.01677   0.01085  -0.0936   0.8947   0.5220
  -3.500  -0.0123   0.01632   0.01021  -0.0964   0.8882   0.5273
  -3.250   0.0256   0.01595   0.00975  -0.0985   0.8814   0.5305
  -3.000   0.0595   0.01573   0.00949  -0.0995   0.8724   0.5332
  -2.750   0.0928   0.01555   0.00925  -0.1005   0.8633   0.5366
  -2.500   0.1277   0.01529   0.00887  -0.1020   0.8544   0.5404
  -2.250   0.1578   0.01505   0.00847  -0.1027   0.8432   0.5445
  -2.000   0.1898   0.01484   0.00822  -0.1035   0.8338   0.5473
  -1.750   0.2189   0.01473   0.00808  -0.1036   0.8230   0.5501
  -1.500   0.2470   0.01463   0.00792  -0.1036   0.8118   0.5534
  -1.250   0.2781   0.01449   0.00768  -0.1042   0.8021   0.5570
  -1.000   0.3074   0.01436   0.00742  -0.1047   0.7910   0.5609
  -0.750   0.3346   0.01426   0.00730  -0.1045   0.7798   0.5638
  -0.500   0.3639   0.01422   0.00722  -0.1046   0.7699   0.5669
  -0.250   0.3913   0.01417   0.00714  -0.1045   0.7587   0.5704
   0.000   0.4189   0.01413   0.00703  -0.1045   0.7476   0.5742
   0.250   0.4489   0.01408   0.00686  -0.1050   0.7377   0.5782
   0.500   0.4752   0.01402   0.00683  -0.1046   0.7265   0.5810
   0.750   0.5019   0.01403   0.00684  -0.1043   0.7156   0.5845
   1.000   0.5307   0.01404   0.00679  -0.1045   0.7058   0.5887
   1.250   0.5579   0.01404   0.00674  -0.1044   0.6944   0.5931
   1.500   0.5847   0.01403   0.00673  -0.1042   0.6835   0.5965
   1.750   0.6126   0.01406   0.00674  -0.1041   0.6736   0.5999
   2.000   0.6388   0.01410   0.00679  -0.1038   0.6622   0.6042
   2.250   0.6660   0.01416   0.00682  -0.1037   0.6511   0.6093
   2.500   0.6936   0.01419   0.00683  -0.1036   0.6410   0.6133
   2.750   0.7192   0.01424   0.00692  -0.1031   0.6294   0.6172
   3.000   0.7454   0.01431   0.00701  -0.1028   0.6180   0.6219
   3.250   0.7730   0.01440   0.00703  -0.1028   0.6069   0.6273
   3.500   0.7987   0.01445   0.00713  -0.1023   0.5956   0.6315
   3.750   0.8236   0.01453   0.00727  -0.1017   0.5834   0.6368
   4.000   0.8501   0.01465   0.00736  -0.1014   0.5717   0.6429
   4.250   0.8759   0.01474   0.00747  -0.1010   0.5605   0.6475
   4.500   0.9006   0.01484   0.00762  -0.1004   0.5482   0.6532
   4.750   0.9258   0.01497   0.00777  -0.0999   0.5356   0.6599
   5.000   0.9500   0.01508   0.00796  -0.0991   0.5236   0.6656
   5.250   0.9751   0.01524   0.00811  -0.0986   0.5115   0.6730
   5.500   0.9993   0.01538   0.00829  -0.0979   0.4991   0.6797
   5.750   1.0224   0.01552   0.00852  -0.0970   0.4858   0.6871
   6.000   1.0458   0.01568   0.00874  -0.0962   0.4727   0.6949
   6.250   1.0686   0.01586   0.00898  -0.0952   0.4595   0.7035
   6.500   1.0909   0.01605   0.00922  -0.0942   0.4458   0.7127
   6.750   1.1128   0.01627   0.00947  -0.0932   0.4319   0.7235
   7.000   1.1332   0.01648   0.00975  -0.0918   0.4174   0.7335
   7.250   1.1532   0.01671   0.01004  -0.0903   0.4021   0.7451
   7.500   1.1722   0.01696   0.01036  -0.0888   0.3862   0.7585
   7.750   1.1901   0.01722   0.01071  -0.0870   0.3697   0.7736
   8.000   1.2063   0.01750   0.01108  -0.0849   0.3527   0.7907
   8.250   1.2207   0.01779   0.01147  -0.0825   0.3349   0.8110
   8.500   1.2330   0.01810   0.01188  -0.0797   0.3166   0.8377
   8.750   1.2390   0.01833   0.01222  -0.0756   0.2993   0.8817
   9.000   1.2466   0.01862   0.01255  -0.0722   0.2808   1.0000
   9.250   1.2592   0.01935   0.01317  -0.0702   0.2599   1.0000
   9.500   1.2701   0.02013   0.01389  -0.0679   0.2386   1.0000
   9.750   1.2782   0.02106   0.01471  -0.0654   0.2189   1.0000
  10.000   1.2852   0.02210   0.01567  -0.0628   0.2007   1.0000
  10.250   1.2924   0.02318   0.01670  -0.0604   0.1833   1.0000
  10.500   1.2984   0.02437   0.01785  -0.0580   0.1676   1.0000
  10.750   1.3034   0.02568   0.01912  -0.0556   0.1536   1.0000
  11.000   1.3072   0.02714   0.02053  -0.0534   0.1409   1.0000
  11.250   1.3096   0.02877   0.02211  -0.0512   0.1295   1.0000
  11.500   1.3146   0.03032   0.02371  -0.0495   0.1185   1.0000
  11.750   1.3180   0.03207   0.02548  -0.0478   0.1087   1.0000
  12.000   1.3181   0.03416   0.02753  -0.0461   0.1007   1.0000
  12.250   1.3213   0.03609   0.02951  -0.0448   0.0926   1.0000
  12.500   1.3223   0.03831   0.03177  -0.0436   0.0857   1.0000
  12.750   1.3227   0.04066   0.03412  -0.0426   0.0795   1.0000
  13.000   1.3237   0.04309   0.03662  -0.0417   0.0738   1.0000
  13.250   1.3240   0.04564   0.03921  -0.0411   0.0688   1.0000
  13.500   1.3228   0.04845   0.04206  -0.0405   0.0644   1.0000
  13.750   1.3242   0.05110   0.04482  -0.0402   0.0600   1.0000
  14.000   1.3214   0.05424   0.04791  -0.0399   0.0566   1.0000
  14.250   1.3229   0.05707   0.05091  -0.0398   0.0531   1.0000
  14.500   1.3231   0.06011   0.05402  -0.0400   0.0500   1.0000
  14.750   1.3219   0.06330   0.05712  -0.0399   0.0471   1.0000
  15.000   1.3226   0.06652   0.06056  -0.0404   0.0448   1.0000
  15.250   1.3226   0.06984   0.06398  -0.0409   0.0423   1.0000
  15.500   1.3221   0.07323   0.06737  -0.0416   0.0402   1.0000
  15.750   1.3227   0.07657   0.07081  -0.0419   0.0382   1.0000
  16.000   1.3219   0.08029   0.07469  -0.0429   0.0364   1.0000
  16.250   1.3214   0.08394   0.07843  -0.0439   0.0347   1.0000
  16.500   1.3230   0.08719   0.08165  -0.0447   0.0330   1.0000
  16.750   1.3216   0.09114   0.08576  -0.0457   0.0316   1.0000
  17.000   1.3177   0.09561   0.09042  -0.0474   0.0304   1.0000
  17.250   1.3151   0.09987   0.09481  -0.0491   0.0292   1.0000
  17.500   1.3150   0.10368   0.09867  -0.0506   0.0280   1.0000
  17.750   1.3198   0.10649   0.10143  -0.0510   0.0267   1.0000
  18.000   1.3108   0.11215   0.10734  -0.0539   0.0261   1.0000
  18.250   1.3020   0.11784   0.11326  -0.0569   0.0254   1.0000
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