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EPPLER 558 AIRFOIL (e558-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 558 AIRFOIL (e558-il)
Reynolds number: 50,000
Max Cl/Cd: 29.7 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e558-il-50000-n5.txt
Download as CSV file: xf-e558-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 558 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.4025   0.12124   0.11358  -0.0435   1.0000   0.0608
 -12.500  -0.4198   0.11307   0.10548  -0.0469   1.0000   0.0622
 -12.250  -0.4493   0.10221   0.09471  -0.0517   1.0000   0.0628
 -12.000  -0.4308   0.10332   0.09588  -0.0499   1.0000   0.0656
 -11.750  -0.4455   0.09671   0.08934  -0.0524   1.0000   0.0679
 -11.500  -0.4946   0.08349   0.07613  -0.0589   1.0000   0.0672
 -11.250  -0.5326   0.07394   0.06648  -0.0636   1.0000   0.0672
 -11.000  -0.5552   0.06780   0.06026  -0.0661   1.0000   0.0679
 -10.750  -0.5735   0.06283   0.05519  -0.0677   1.0000   0.0691
 -10.500  -0.5923   0.05828   0.05051  -0.0687   1.0000   0.0709
 -10.250  -0.6103   0.05436   0.04644  -0.0690   1.0000   0.0725
 -10.000  -0.6182   0.05236   0.04462  -0.0676   1.0000   0.0750
  -9.750  -0.6333   0.04988   0.04216  -0.0664   1.0000   0.0769
  -9.500  -0.6454   0.04715   0.03936  -0.0656   1.0000   0.0799
  -9.250  -0.6549   0.04462   0.03673  -0.0642   1.0000   0.0840
  -9.000  -0.6586   0.04285   0.03508  -0.0627   1.0000   0.0888
  -8.750  -0.6620   0.04067   0.03278  -0.0614   1.0000   0.0958
  -8.500  -0.6610   0.03904   0.03123  -0.0600   1.0000   0.1038
  -8.250  -0.6577   0.03745   0.02968  -0.0589   1.0000   0.1144
  -8.000  -0.6514   0.03604   0.02829  -0.0580   1.0000   0.1270
  -7.750  -0.6424   0.03492   0.02718  -0.0572   1.0000   0.1417
  -7.500  -0.6238   0.03398   0.02616  -0.0579   0.9974   0.1610
  -7.250  -0.5850   0.03356   0.02572  -0.0616   0.9873   0.1853
  -7.000  -0.5472   0.03316   0.02516  -0.0648   0.9768   0.2084
  -6.750  -0.5103   0.03282   0.02464  -0.0675   0.9660   0.2286
  -6.500  -0.4738   0.03266   0.02436  -0.0697   0.9551   0.2458
  -6.250  -0.4357   0.03239   0.02393  -0.0721   0.9449   0.2624
  -6.000  -0.4020   0.03193   0.02325  -0.0739   0.9328   0.2778
  -5.750  -0.3682   0.03187   0.02313  -0.0749   0.9211   0.2904
  -5.500  -0.3311   0.03159   0.02273  -0.0767   0.9111   0.3033
  -5.250  -0.2952   0.03111   0.02207  -0.0785   0.9002   0.3167
  -5.000  -0.2617   0.03053   0.02124  -0.0801   0.8884   0.3302
  -4.750  -0.2202   0.03017   0.02077  -0.0823   0.8806   0.3423
  -4.500  -0.1892   0.02982   0.02031  -0.0829   0.8679   0.3530
  -4.250  -0.1519   0.02921   0.01946  -0.0850   0.8578   0.3660
  -4.000  -0.1145   0.02887   0.01904  -0.0864   0.8478   0.3768
  -3.750  -0.0825   0.02845   0.01848  -0.0872   0.8357   0.3872
  -3.500  -0.0412   0.02783   0.01759  -0.0898   0.8273   0.4007
  -3.250  -0.0133   0.02765   0.01741  -0.0894   0.8138   0.4087
  -3.000   0.0193   0.02723   0.01679  -0.0904   0.8020   0.4205
  -2.750   0.0556   0.02687   0.01636  -0.0915   0.7923   0.4306
  -2.500   0.0838   0.02662   0.01598  -0.0916   0.7790   0.4409
  -2.250   0.1152   0.02638   0.01562  -0.0921   0.7676   0.4517
  -2.000   0.1486   0.02608   0.01523  -0.0928   0.7570   0.4619
  -1.750   0.1761   0.02594   0.01493  -0.0928   0.7440   0.4736
  -1.500   0.2059   0.02578   0.01474  -0.0928   0.7332   0.4832
  -1.250   0.2364   0.02561   0.01444  -0.0932   0.7221   0.4948
  -1.000   0.2623   0.02558   0.01437  -0.0927   0.7099   0.5056
  -0.750   0.2941   0.02542   0.01411  -0.0931   0.7003   0.5171
  -0.500   0.3203   0.02543   0.01405  -0.0929   0.6884   0.5297
  -0.250   0.3471   0.02543   0.01403  -0.0925   0.6777   0.5410
   0.000   0.3766   0.02537   0.01391  -0.0925   0.6678   0.5536
   0.250   0.4015   0.02547   0.01398  -0.0921   0.6568   0.5671
   0.500   0.4325   0.02539   0.01384  -0.0923   0.6483   0.5816
   0.750   0.4545   0.02557   0.01407  -0.0913   0.6370   0.5948
   1.000   0.4840   0.02555   0.01402  -0.0913   0.6288   0.6108
   1.250   0.5065   0.02574   0.01428  -0.0904   0.6184   0.6270
   1.500   0.5344   0.02576   0.01430  -0.0901   0.6103   0.6452
   1.750   0.5564   0.02596   0.01459  -0.0891   0.6004   0.6645
   2.000   0.5836   0.02599   0.01464  -0.0886   0.5930   0.6872
   2.250   0.6034   0.02626   0.01504  -0.0872   0.5834   0.7114
   2.500   0.6302   0.02619   0.01503  -0.0864   0.5769   0.7410
   2.750   0.6451   0.02652   0.01556  -0.0841   0.5673   0.7750
   3.000   0.6692   0.02645   0.01559  -0.0828   0.5607   0.8237
   3.250   0.6940   0.02667   0.01601  -0.0823   0.5520   0.9101
   3.500   0.7300   0.02690   0.01612  -0.0843   0.5443   1.0000
   3.750   0.7552   0.02749   0.01663  -0.0845   0.5365   1.0000
   4.000   0.7806   0.02803   0.01711  -0.0845   0.5289   1.0000
   4.250   0.8112   0.02837   0.01731  -0.0851   0.5229   1.0000
   4.500   0.8283   0.02924   0.01823  -0.0841   0.5143   1.0000
   4.750   0.8577   0.02961   0.01853  -0.0844   0.5083   1.0000
   5.000   0.8764   0.03046   0.01941  -0.0835   0.5009   1.0000
   5.250   0.8989   0.03112   0.02007  -0.0830   0.4939   1.0000
   5.500   0.9314   0.03136   0.02024  -0.0835   0.4889   1.0000
   5.750   0.9400   0.03269   0.02171  -0.0815   0.4806   1.0000
   6.000   0.9658   0.03321   0.02222  -0.0813   0.4747   1.0000
   6.250   0.9875   0.03397   0.02301  -0.0807   0.4686   1.0000
   6.500   0.9992   0.03518   0.02434  -0.0790   0.4612   1.0000
   6.750   1.0281   0.03556   0.02471  -0.0791   0.4560   1.0000
   7.000   1.0374   0.03694   0.02622  -0.0772   0.4491   1.0000
   7.250   1.0518   0.03802   0.02739  -0.0758   0.4423   1.0000
   7.500   1.0850   0.03819   0.02754  -0.0763   0.4377   1.0000
   7.750   1.0766   0.04049   0.03003  -0.0728   0.4297   1.0000
   8.000   1.0959   0.04130   0.03092  -0.0719   0.4237   1.0000
   8.250   1.1314   0.04132   0.03094  -0.0725   0.4192   1.0000
   8.500   1.0962   0.04497   0.03481  -0.0668   0.4102   1.0000
   8.750   1.1274   0.04508   0.03496  -0.0669   0.4051   1.0000
   9.000   1.1037   0.04848   0.03848  -0.0629   0.3974   1.0000
   9.250   1.0988   0.05096   0.04106  -0.0609   0.3901   1.0000
   9.500   1.1506   0.04946   0.03962  -0.0617   0.3865   1.0000
   9.750   1.0615   0.05920   0.04947  -0.0578   0.3731   1.0000
  10.000   1.1069   0.05743   0.04779  -0.0572   0.3702   1.0000
  10.250   1.0353   0.06807   0.05850  -0.0575   0.3553   1.0000
  10.500   1.0769   0.06607   0.05659  -0.0561   0.3529   1.0000
  11.000   1.0516   0.07548   0.06615  -0.0567   0.3348   1.0000
  11.500   0.9843   0.09192   0.08271  -0.0609   0.3090   1.0000
  11.750   1.0103   0.09153   0.08243  -0.0597   0.3049   1.0000
  12.250   1.0085   0.09875   0.08982  -0.0608   0.2888   1.0000
  12.750   1.0079   0.10590   0.09714  -0.0621   0.2730   1.0000
  13.250   1.0094   0.11280   0.10421  -0.0635   0.2573   1.0000
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