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E63 (4.25%) (e63-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E63 (4.25%) (e63-il)
Reynolds number: 50,000
Max Cl/Cd: 51.1 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e63-il-50000-n5.txt
Download as CSV file: xf-e63-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E63  (4.25%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3633   0.11634   0.10945  -0.0220   1.0000   0.0585
  -7.500  -0.3685   0.11553   0.10875  -0.0216   1.0000   0.0590
  -7.250  -0.3745   0.11473   0.10806  -0.0210   1.0000   0.0593
  -7.000  -0.3758   0.11346   0.10689  -0.0221   1.0000   0.0595
  -6.750  -0.3693   0.10862   0.10212  -0.0201   1.0000   0.0604
  -6.500  -0.3627   0.10453   0.09805  -0.0181   1.0000   0.0623
  -6.250  -0.3598   0.10192   0.09550  -0.0175   1.0000   0.0642
  -6.000  -0.3571   0.09951   0.09316  -0.0175   1.0000   0.0663
  -5.750  -0.3536   0.09730   0.09103  -0.0185   1.0000   0.0687
  -5.500  -0.3464   0.09571   0.08952  -0.0229   1.0000   0.0711
  -5.250  -0.3290   0.09403   0.08786  -0.0317   1.0000   0.0719
  -5.000  -0.3329   0.08921   0.08314  -0.0239   1.0000   0.0742
  -4.750  -0.3259   0.08623   0.08021  -0.0233   1.0000   0.0784
  -4.500  -0.3025   0.08382   0.07778  -0.0321   1.0000   0.0843
  -4.250  -0.2918   0.08011   0.07414  -0.0330   1.0000   0.0868
  -4.000  -0.2833   0.07707   0.07114  -0.0319   1.0000   0.0922
  -3.750  -0.2498   0.07346   0.06748  -0.0418   1.0000   0.0998
  -3.500  -0.2404   0.07037   0.06444  -0.0403   1.0000   0.1053
  -3.250  -0.2061   0.06653   0.06054  -0.0483   1.0000   0.1145
  -3.000  -0.1657   0.06271   0.05651  -0.0571   1.0000   0.1268
  -2.750  -0.1392   0.05946   0.05321  -0.0603   1.0000   0.1371
  -2.500  -0.1087   0.05583   0.04955  -0.0644   1.0000   0.1456
  -2.250   0.0318   0.04563   0.03814  -0.0934   1.0000   0.0472
  -2.000   0.0656   0.04206   0.03458  -0.0971   1.0000   0.0434
  -1.750   0.1370   0.03723   0.02911  -0.1084   1.0000   0.0384
  -1.500   0.2005   0.03375   0.02474  -0.1164   1.0000   0.0359
  -1.250   0.2490   0.03119   0.02160  -0.1213   1.0000   0.0358
  -1.000   0.2920   0.02918   0.01916  -0.1249   1.0000   0.0381
  -0.750   0.3281   0.02809   0.01759  -0.1269   1.0000   0.0455
  -0.500   0.3640   0.02692   0.01605  -0.1285   1.0000   0.0496
  -0.250   0.3956   0.02613   0.01493  -0.1291   1.0000   0.0545
   0.000   0.4290   0.02548   0.01402  -0.1301   1.0000   0.0658
   0.250   0.4750   0.02253   0.01348  -0.1338   1.0000   0.7517
   0.750   0.5126   0.02340   0.01356  -0.1313   1.0000   1.0000
   1.000   0.5411   0.02403   0.01383  -0.1322   0.9967   1.0000
   1.250   0.5794   0.02465   0.01418  -0.1349   0.9874   1.0000
   1.500   0.6172   0.02518   0.01452  -0.1374   0.9776   1.0000
   1.750   0.6546   0.02562   0.01485  -0.1398   0.9672   1.0000
   2.000   0.6916   0.02599   0.01515  -0.1421   0.9561   1.0000
   2.250   0.7286   0.02628   0.01545  -0.1442   0.9445   1.0000
   2.500   0.7654   0.02649   0.01568  -0.1462   0.9320   1.0000
   2.750   0.8020   0.02663   0.01588  -0.1480   0.9186   1.0000
   3.000   0.8383   0.02669   0.01606  -0.1496   0.9043   1.0000
   3.250   0.8751   0.02666   0.01624  -0.1511   0.8892   1.0000
   3.500   0.9131   0.02648   0.01625  -0.1526   0.8735   1.0000
   3.750   0.9521   0.02613   0.01613  -0.1540   0.8570   1.0000
   4.000   0.9852   0.02583   0.01609  -0.1541   0.8357   1.0000
   4.250   1.0225   0.02526   0.01596  -0.1546   0.8140   1.0000
   4.500   1.0588   0.02468   0.01571  -0.1547   0.7866   1.0000
   4.750   1.0971   0.02405   0.01543  -0.1549   0.7515   1.0000
   5.000   1.1388   0.02344   0.01510  -0.1554   0.7013   1.0000
   5.250   1.1809   0.02311   0.01498  -0.1557   0.6235   1.0000
   5.500   1.2099   0.02370   0.01528  -0.1542   0.5199   1.0000
   5.750   1.2233   0.02526   0.01616  -0.1507   0.3946   1.0000
   6.000   1.2287   0.02771   0.01754  -0.1472   0.2448   1.0000
   6.250   1.2396   0.03081   0.01944  -0.1455   0.1078   1.0000
   6.500   1.2573   0.03356   0.02193  -0.1439   0.0649   1.0000
   6.750   1.2749   0.03595   0.02445  -0.1420   0.0531   1.0000
   7.000   1.2926   0.03831   0.02698  -0.1401   0.0472   1.0000
   7.250   1.3148   0.04095   0.02990  -0.1386   0.0438   1.0000
   7.500   1.3431   0.04396   0.03330  -0.1379   0.0409   1.0000
   7.750   1.3669   0.04692   0.03658  -0.1370   0.0372   1.0000
   8.000   1.3854   0.05040   0.04054  -0.1358   0.0333   1.0000
   8.250   1.4039   0.05412   0.04494  -0.1340   0.0314   1.0000
   8.500   1.4174   0.05852   0.04997  -0.1317   0.0307   1.0000
   8.750   1.4241   0.06312   0.05519  -0.1289   0.0303   1.0000
   9.000   1.4246   0.06779   0.06042  -0.1257   0.0301   1.0000
   9.250   1.4195   0.07248   0.06563  -0.1223   0.0300   1.0000
   9.500   1.4090   0.07716   0.07074  -0.1188   0.0300   1.0000
   9.750   1.3933   0.08140   0.07533  -0.1150   0.0301   1.0000
  10.000   1.3745   0.08585   0.08009  -0.1119   0.0301   1.0000
  10.250   1.3542   0.09069   0.08520  -0.1098   0.0303   1.0000
  10.500   1.3329   0.09602   0.09078  -0.1090   0.0304   1.0000
  10.750   1.3119   0.10187   0.09684  -0.1098   0.0306   1.0000
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