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EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 68 AIRFOIL (e68-il)
Reynolds number: 50,000
Max Cl/Cd: 32.74 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e68-il-50000-n5.txt
Download as CSV file: xf-e68-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 68 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3991   0.10647   0.09937  -0.0517   1.0000   0.0522
 -10.250  -0.4106   0.10180   0.09481  -0.0525   1.0000   0.0515
 -10.000  -0.4255   0.09670   0.08983  -0.0535   1.0000   0.0509
  -9.750  -0.4684   0.08569   0.07897  -0.0589   1.0000   0.0488
  -9.500  -0.4874   0.08125   0.07460  -0.0594   1.0000   0.0486
  -9.250  -0.5116   0.07709   0.07053  -0.0596   1.0000   0.0483
  -9.000  -0.5396   0.07381   0.06731  -0.0586   1.0000   0.0479
  -8.750  -0.5671   0.07084   0.06438  -0.0569   1.0000   0.0476
  -8.500  -0.5915   0.06723   0.06070  -0.0556   1.0000   0.0474
  -8.250  -0.6112   0.06345   0.05678  -0.0544   1.0000   0.0473
  -8.000  -0.6255   0.05951   0.05261  -0.0533   1.0000   0.0473
  -7.750  -0.6341   0.05546   0.04822  -0.0524   1.0000   0.0475
  -7.500  -0.6360   0.05155   0.04388  -0.0516   1.0000   0.0479
  -7.250  -0.6284   0.04755   0.03930  -0.0517   0.9987   0.0486
  -7.000  -0.6050   0.04425   0.03565  -0.0536   0.9942   0.0501
  -6.750  -0.5800   0.04184   0.03298  -0.0551   0.9893   0.0524
  -6.500  -0.5523   0.03963   0.03033  -0.0568   0.9847   0.0568
  -6.250  -0.5258   0.03748   0.02778  -0.0578   0.9801   0.0619
  -6.000  -0.4979   0.03590   0.02605  -0.0588   0.9751   0.0677
  -5.750  -0.4675   0.03440   0.02435  -0.0602   0.9710   0.0771
  -5.500  -0.4419   0.03316   0.02297  -0.0606   0.9653   0.0897
  -5.250  -0.4119   0.03211   0.02182  -0.0619   0.9604   0.1077
  -5.000  -0.3835   0.03113   0.02076  -0.0628   0.9554   0.1301
  -4.750  -0.3558   0.03027   0.01984  -0.0635   0.9497   0.1560
  -4.500  -0.3233   0.02951   0.01913  -0.0652   0.9452   0.1873
  -4.250  -0.2982   0.02887   0.01854  -0.0654   0.9389   0.2194
  -4.000  -0.2676   0.02833   0.01805  -0.0666   0.9335   0.2616
  -3.750  -0.2377   0.02789   0.01773  -0.0677   0.9283   0.3085
  -3.500  -0.2120   0.02755   0.01750  -0.0678   0.9217   0.3562
  -3.250  -0.1792   0.02733   0.01735  -0.0690   0.9168   0.4127
  -3.000  -0.1566   0.02719   0.01731  -0.0683   0.9097   0.4611
  -2.750  -0.1273   0.02712   0.01731  -0.0685   0.9040   0.5141
  -2.500  -0.1021   0.02711   0.01735  -0.0679   0.8977   0.5620
  -2.250  -0.0776   0.02713   0.01740  -0.0670   0.8909   0.6074
  -2.000  -0.0484   0.02717   0.01747  -0.0668   0.8859   0.6529
  -1.750  -0.0308   0.02726   0.01758  -0.0646   0.8776   0.6917
  -1.500  -0.0021   0.02731   0.01760  -0.0641   0.8725   0.7347
  -1.250   0.0130   0.02741   0.01772  -0.0614   0.8640   0.7719
  -1.000   0.0400   0.02743   0.01771  -0.0605   0.8585   0.8139
  -0.750   0.0582   0.02752   0.01778  -0.0584   0.8503   0.8561
  -0.500   0.0951   0.02754   0.01773  -0.0597   0.8450   0.9043
  -0.250   0.1478   0.02763   0.01771  -0.0648   0.8399   0.9568
   0.000   0.1873   0.02772   0.01761  -0.0682   0.8322   1.0000
   0.250   0.2183   0.02781   0.01751  -0.0696   0.8260   1.0000
   0.500   0.2403   0.02805   0.01760  -0.0695   0.8171   1.0000
   0.750   0.2697   0.02824   0.01764  -0.0704   0.8102   1.0000
   1.000   0.2956   0.02850   0.01778  -0.0707   0.8021   1.0000
   1.250   0.3228   0.02876   0.01793  -0.0711   0.7946   1.0000
   1.500   0.3511   0.02900   0.01808  -0.0716   0.7870   1.0000
   1.750   0.3758   0.02933   0.01834  -0.0716   0.7786   1.0000
   2.000   0.4066   0.02950   0.01845  -0.0724   0.7717   1.0000
   2.250   0.4290   0.02990   0.01882  -0.0719   0.7625   1.0000
   2.500   0.4624   0.02998   0.01886  -0.0729   0.7564   1.0000
   2.750   0.4826   0.03046   0.01932  -0.0721   0.7463   1.0000
   3.000   0.5188   0.03039   0.01926  -0.0733   0.7408   1.0000
   3.500   0.5761   0.03072   0.01961  -0.0737   0.7252   1.0000
   3.750   0.5929   0.03130   0.02022  -0.0724   0.7136   1.0000
   4.000   0.6156   0.03167   0.02065  -0.0717   0.7036   1.0000
   4.250   0.6511   0.03149   0.02052  -0.0725   0.6971   1.0000
   4.500   0.6700   0.03199   0.02107  -0.0714   0.6856   1.0000
   4.750   0.6987   0.03205   0.02124  -0.0713   0.6768   1.0000
   5.000   0.7298   0.03197   0.02124  -0.0714   0.6680   1.0000
   5.250   0.7499   0.03238   0.02174  -0.0703   0.6562   1.0000
   5.500   0.7766   0.03244   0.02191  -0.0699   0.6458   1.0000
   5.750   0.8142   0.03197   0.02159  -0.0705   0.6375   1.0000
   6.000   0.8348   0.03225   0.02198  -0.0693   0.6245   1.0000
   6.250   0.8579   0.03240   0.02225  -0.0683   0.6116   1.0000
   6.750   0.9099   0.03233   0.02247  -0.0667   0.5856   1.0000
   7.000   0.9361   0.03222   0.02251  -0.0658   0.5713   1.0000
   7.250   0.9608   0.03216   0.02258  -0.0647   0.5556   1.0000
   7.500   0.9849   0.03209   0.02268  -0.0635   0.5387   1.0000
   7.750   1.0107   0.03192   0.02263  -0.0624   0.5206   1.0000
   8.000   1.0320   0.03198   0.02279  -0.0609   0.5009   1.0000
   8.250   1.0470   0.03237   0.02329  -0.0587   0.4790   1.0000
   8.500   1.0659   0.03256   0.02357  -0.0569   0.4561   1.0000
   8.750   1.0802   0.03304   0.02409  -0.0547   0.4315   1.0000
   9.000   1.0914   0.03373   0.02483  -0.0523   0.4056   1.0000
   9.250   1.1021   0.03451   0.02560  -0.0500   0.3789   1.0000
   9.500   1.1108   0.03547   0.02652  -0.0476   0.3518   1.0000
   9.750   1.1176   0.03663   0.02762  -0.0452   0.3248   1.0000
  10.000   1.1219   0.03805   0.02899  -0.0428   0.2983   1.0000
  10.250   1.1249   0.03969   0.03063  -0.0406   0.2727   1.0000
  10.500   1.1272   0.04148   0.03236  -0.0385   0.2488   1.0000
  10.750   1.1282   0.04347   0.03428  -0.0366   0.2263   1.0000
  11.000   1.1293   0.04561   0.03639  -0.0349   0.2054   1.0000
  11.250   1.1297   0.04790   0.03866  -0.0333   0.1860   1.0000
  11.500   1.1298   0.05032   0.04103  -0.0320   0.1690   1.0000
  11.750   1.1293   0.05290   0.04355  -0.0308   0.1532   1.0000
  12.000   1.1294   0.05557   0.04624  -0.0298   0.1384   1.0000
  12.250   1.1283   0.05844   0.04910  -0.0290   0.1249   1.0000
  12.500   1.1273   0.06137   0.05205  -0.0283   0.1131   1.0000
  12.750   1.1261   0.06449   0.05529  -0.0279   0.1016   1.0000
  13.000   1.1255   0.06768   0.05858  -0.0276   0.0917   1.0000
  13.250   1.1244   0.07097   0.06190  -0.0275   0.0836   1.0000
  13.500   1.1234   0.07431   0.06531  -0.0275   0.0764   1.0000
  13.750   1.1240   0.07773   0.06889  -0.0275   0.0701   1.0000
  14.000   1.1234   0.08120   0.07244  -0.0277   0.0649   1.0000
  14.250   1.1247   0.08467   0.07602  -0.0279   0.0606   1.0000
  14.500   1.1233   0.08870   0.08032  -0.0285   0.0567   1.0000
  14.750   1.1225   0.09242   0.08414  -0.0292   0.0536   1.0000
  15.000   1.1245   0.09589   0.08764  -0.0296   0.0511   1.0000
  15.250   1.1190   0.10107   0.09318  -0.0310   0.0496   1.0000
  15.500   1.1100   0.10687   0.09929  -0.0331   0.0484   1.0000
  15.750   1.0980   0.11336   0.10606  -0.0359   0.0476   1.0000
  16.000   1.0825   0.12081   0.11377  -0.0397   0.0471   1.0000
  16.250   1.0624   0.12974   0.12295  -0.0448   0.0470   1.0000
  16.500   1.0354   0.14118   0.13461  -0.0518   0.0475   1.0000
  16.750   1.0035   0.15551   0.14904  -0.0606   0.0484   1.0000
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