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E203 (13.64%) (e203-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E203 (13.64%) (e203-il)
Reynolds number: 100,000
Max Cl/Cd: 54.73 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e203-il-100000.txt
Download as CSV file: xf-e203-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E203  (13.64%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3886   0.10240   0.09744  -0.0403   1.0000   0.1482
  -9.750  -0.4635   0.08076   0.07602  -0.0556   1.0000   0.0849
  -9.500  -0.5048   0.06987   0.06519  -0.0624   1.0000   0.0754
  -9.250  -0.5553   0.06434   0.05971  -0.0640   1.0000   0.0738
  -9.000  -0.6427   0.05898   0.05382  -0.0611   1.0000   0.0696
  -8.750  -0.6395   0.05554   0.05038  -0.0591   1.0000   0.0674
  -8.500  -0.6484   0.05223   0.04697  -0.0566   1.0000   0.0663
  -8.250  -0.6577   0.04903   0.04358  -0.0539   1.0000   0.0650
  -8.000  -0.6651   0.04581   0.04010  -0.0513   1.0000   0.0638
  -7.750  -0.6693   0.04257   0.03650  -0.0488   1.0000   0.0626
  -7.500  -0.6685   0.03953   0.03303  -0.0466   1.0000   0.0617
  -7.250  -0.6624   0.03694   0.03005  -0.0447   1.0000   0.0615
  -7.000  -0.6524   0.03504   0.02785  -0.0431   1.0000   0.0626
  -6.750  -0.6155   0.03266   0.02496  -0.0461   0.9942   0.0656
  -6.500  -0.5766   0.03032   0.02213  -0.0487   0.9870   0.0676
  -6.250  -0.5376   0.02805   0.01961  -0.0512   0.9808   0.0703
  -6.000  -0.4992   0.02649   0.01807  -0.0538   0.9735   0.0765
  -5.750  -0.4627   0.02505   0.01660  -0.0559   0.9657   0.0861
  -5.500  -0.4244   0.02354   0.01520  -0.0583   0.9587   0.1034
  -5.250  -0.3941   0.02186   0.01384  -0.0597   0.9497   0.1537
  -5.000  -0.3564   0.02021   0.01280  -0.0629   0.9433   0.2557
  -4.750  -0.3287   0.01963   0.01278  -0.0637   0.9329   0.3618
  -4.500  -0.2934   0.01987   0.01305  -0.0650   0.9245   0.4360
  -4.250  -0.2571   0.02010   0.01323  -0.0663   0.9165   0.4794
  -4.000  -0.2259   0.02031   0.01336  -0.0667   0.9077   0.5131
  -3.750  -0.1869   0.02042   0.01341  -0.0683   0.9014   0.5435
  -3.500  -0.1569   0.02052   0.01352  -0.0683   0.8928   0.5659
  -3.250  -0.1177   0.02046   0.01335  -0.0701   0.8870   0.5906
  -3.000  -0.0853   0.02045   0.01332  -0.0705   0.8797   0.6093
  -2.750  -0.0514   0.02036   0.01317  -0.0712   0.8728   0.6278
  -2.500  -0.0134   0.02018   0.01293  -0.0726   0.8678   0.6460
  -2.250   0.0117   0.02018   0.01288  -0.0720   0.8585   0.6611
  -2.000   0.0515   0.01990   0.01253  -0.0737   0.8543   0.6775
  -1.750   0.0723   0.01998   0.01259  -0.0724   0.8441   0.6907
  -1.500   0.1099   0.01971   0.01227  -0.0738   0.8395   0.7055
  -1.250   0.1304   0.01982   0.01235  -0.0726   0.8298   0.7187
  -1.000   0.1657   0.01958   0.01207  -0.0735   0.8248   0.7332
  -0.750   0.1860   0.01972   0.01221  -0.0723   0.8155   0.7470
  -0.500   0.2189   0.01953   0.01198  -0.0729   0.8101   0.7618
  -0.250   0.2391   0.01970   0.01217  -0.0716   0.8014   0.7764
   0.000   0.2694   0.01956   0.01203  -0.0717   0.7956   0.7921
   0.250   0.2903   0.01972   0.01222  -0.0705   0.7875   0.8086
   0.500   0.3171   0.01967   0.01219  -0.0699   0.7812   0.8270
   0.750   0.3399   0.01977   0.01233  -0.0689   0.7742   0.8485
   1.000   0.3634   0.01982   0.01245  -0.0678   0.7671   0.8726
   1.250   0.3999   0.01961   0.01225  -0.0686   0.7629   0.9004
   1.500   0.4323   0.01998   0.01272  -0.0701   0.7537   0.9341
   1.750   0.4961   0.01978   0.01250  -0.0769   0.7492   0.9626
   2.000   0.5605   0.01997   0.01272  -0.0850   0.7416   0.9915
   2.250   0.5806   0.02006   0.01274  -0.0852   0.7348   1.0000
   2.500   0.5909   0.02068   0.01330  -0.0832   0.7262   1.0000
   2.750   0.6182   0.02087   0.01344  -0.0833   0.7199   1.0000
   3.000   0.6372   0.02146   0.01401  -0.0823   0.7119   1.0000
   3.250   0.6648   0.02169   0.01423  -0.0823   0.7052   1.0000
   3.500   0.6858   0.02223   0.01479  -0.0815   0.6973   1.0000
   3.750   0.7133   0.02245   0.01501  -0.0814   0.6901   1.0000
   4.000   0.7345   0.02296   0.01558  -0.0805   0.6817   1.0000
   4.250   0.7642   0.02303   0.01566  -0.0805   0.6744   1.0000
   4.500   0.7839   0.02359   0.01628  -0.0794   0.6650   1.0000
   4.750   0.8179   0.02340   0.01612  -0.0797   0.6581   1.0000
   5.000   0.8360   0.02398   0.01678  -0.0783   0.6476   1.0000
   5.250   0.8726   0.02362   0.01643  -0.0788   0.6406   1.0000
   5.500   0.8932   0.02394   0.01685  -0.0775   0.6293   1.0000
   5.750   0.9165   0.02411   0.01713  -0.0765   0.6183   1.0000
   6.000   0.9487   0.02377   0.01682  -0.0763   0.6084   1.0000
   6.250   0.9790   0.02344   0.01655  -0.0759   0.5971   1.0000
   6.500   1.0025   0.02339   0.01662  -0.0747   0.5839   1.0000
   6.750   1.0280   0.02318   0.01649  -0.0736   0.5700   1.0000
   7.000   1.0543   0.02283   0.01622  -0.0725   0.5553   1.0000
   7.250   1.0809   0.02239   0.01584  -0.0714   0.5391   1.0000
   7.500   1.1076   0.02189   0.01539  -0.0702   0.5216   1.0000
   7.750   1.1254   0.02174   0.01537  -0.0680   0.5007   1.0000
   8.000   1.1460   0.02139   0.01507  -0.0659   0.4775   1.0000
   8.250   1.1601   0.02133   0.01509  -0.0631   0.4494   1.0000
   8.500   1.1718   0.02141   0.01519  -0.0599   0.4152   1.0000
   8.750   1.1777   0.02181   0.01548  -0.0560   0.3723   1.0000
   9.000   1.1769   0.02267   0.01611  -0.0514   0.3212   1.0000
   9.250   1.1690   0.02396   0.01705  -0.0461   0.2747   1.0000
   9.500   1.1597   0.02566   0.01841  -0.0412   0.2344   1.0000
   9.750   1.1510   0.02759   0.02004  -0.0369   0.2009   1.0000
  10.000   1.1440   0.02964   0.02186  -0.0334   0.1723   1.0000
  10.250   1.1390   0.03177   0.02383  -0.0305   0.1476   1.0000
  10.500   1.1343   0.03407   0.02588  -0.0280   0.1280   1.0000
  10.750   1.1326   0.03633   0.02812  -0.0260   0.1087   1.0000
  11.000   1.1313   0.03873   0.03043  -0.0242   0.0929   1.0000
  11.250   1.1317   0.04120   0.03283  -0.0225   0.0793   1.0000
  11.500   1.1363   0.04357   0.03515  -0.0210   0.0683   1.0000
  11.750   1.1455   0.04583   0.03738  -0.0196   0.0598   1.0000
  12.000   1.1620   0.04781   0.03926  -0.0185   0.0540   1.0000
  12.250   1.1856   0.05011   0.04174  -0.0174   0.0496   1.0000
  12.500   1.1984   0.05238   0.04419  -0.0165   0.0465   1.0000
  12.750   1.2171   0.05475   0.04649  -0.0160   0.0433   1.0000
  13.000   1.2302   0.05826   0.05030  -0.0152   0.0418   1.0000
  13.250   1.2315   0.06157   0.05395  -0.0141   0.0412   1.0000
  13.500   1.2281   0.06522   0.05792  -0.0132   0.0408   1.0000
  13.750   1.2199   0.06924   0.06226  -0.0126   0.0406   1.0000
  14.000   1.2077   0.07366   0.06700  -0.0123   0.0404   1.0000
  14.250   1.1941   0.07831   0.07192  -0.0126   0.0405   1.0000
  14.500   1.1774   0.08344   0.07732  -0.0133   0.0407   1.0000
  14.750   1.1572   0.08910   0.08324  -0.0148   0.0408   1.0000
  15.000   1.1375   0.09504   0.08941  -0.0168   0.0411   1.0000
  15.250   1.1152   0.10166   0.09625  -0.0196   0.0413   1.0000
  15.500   1.0938   0.10866   0.10343  -0.0229   0.0416   1.0000
  15.750   1.0724   0.11622   0.11115  -0.0269   0.0420   1.0000
  16.000   1.0516   0.12438   0.11945  -0.0314   0.0424   1.0000
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