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E471 (6.25%) (e471-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E471 (6.25%) (e471-il)
Reynolds number: 100,000
Max Cl/Cd: 72.98 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e471-il-100000.txt
Download as CSV file: xf-e471-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E471  (6.25%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3793   0.09998   0.09555  -0.0212   1.0000   0.0639
  -6.750  -0.3919   0.09915   0.09482  -0.0195   1.0000   0.0650
  -6.500  -0.4003   0.09822   0.09398  -0.0216   1.0000   0.0660
  -6.250  -0.4004   0.09676   0.09258  -0.0272   1.0000   0.0666
  -6.000  -0.3965   0.09311   0.08899  -0.0305   1.0000   0.0672
  -5.750  -0.3994   0.08905   0.08495  -0.0201   1.0000   0.0695
  -5.500  -0.3967   0.08652   0.08246  -0.0184   1.0000   0.0729
  -5.250  -0.3908   0.08383   0.07979  -0.0210   1.0000   0.0771
  -5.000  -0.3617   0.07938   0.07527  -0.0378   1.0000   0.0810
  -4.750  -0.3689   0.07661   0.07260  -0.0290   1.0000   0.0832
  -4.500  -0.3600   0.07379   0.06978  -0.0288   1.0000   0.0868
  -4.250  -0.3157   0.06812   0.06393  -0.0453   1.0000   0.0952
  -4.000  -0.3138   0.06550   0.06136  -0.0408   1.0000   0.0977
  -3.750  -0.2678   0.06045   0.05607  -0.0534   1.0000   0.1092
  -3.500  -0.2604   0.05793   0.05362  -0.0505   1.0000   0.1128
  -3.250  -0.2220   0.05367   0.04919  -0.0581   1.0000   0.1251
  -3.000  -0.1697   0.05042   0.04555  -0.0687   1.0000   0.1496
  -2.750  -0.1577   0.04715   0.04244  -0.0669   1.0000   0.1543
  -2.500  -0.1251   0.04449   0.03966  -0.0708   1.0000   0.1812
  -2.000   0.0043   0.03389   0.02771  -0.0910   1.0000   0.1387
  -1.750   0.0854   0.02705   0.01893  -0.0990   1.0000   0.0676
  -1.500   0.1179   0.02563   0.01717  -0.1001   1.0000   0.0659
  -1.250   0.1495   0.02447   0.01572  -0.1009   1.0000   0.0658
  -1.000   0.1798   0.02355   0.01464  -0.1017   1.0000   0.0681
  -0.750   0.2071   0.02314   0.01422  -0.1021   1.0000   0.0776
  -0.500   0.2470   0.02259   0.01371  -0.1046   0.9968   0.0899
  -0.250   0.2967   0.02063   0.01346  -0.1090   0.9966   0.5470
   0.000   0.3210   0.02016   0.01360  -0.1080   0.9883   1.0000
   0.250   0.3622   0.02087   0.01394  -0.1112   0.9820   1.0000
   0.500   0.3984   0.02139   0.01423  -0.1135   0.9736   1.0000
   0.750   0.4354   0.02193   0.01459  -0.1158   0.9657   1.0000
   1.000   0.4759   0.02245   0.01496  -0.1187   0.9583   1.0000
   1.250   0.5095   0.02285   0.01526  -0.1204   0.9487   1.0000
   1.500   0.5469   0.02326   0.01559  -0.1226   0.9402   1.0000
   1.750   0.5882   0.02360   0.01587  -0.1255   0.9322   1.0000
   2.000   0.6219   0.02388   0.01615  -0.1269   0.9217   1.0000
   2.250   0.6586   0.02410   0.01638  -0.1287   0.9116   1.0000
   2.500   0.7046   0.02414   0.01644  -0.1320   0.9036   1.0000
   2.750   0.7422   0.02414   0.01651  -0.1337   0.8926   1.0000
   3.000   0.7790   0.02408   0.01657  -0.1351   0.8808   1.0000
   3.250   0.8183   0.02385   0.01645  -0.1367   0.8691   1.0000
   3.500   0.8610   0.02338   0.01612  -0.1386   0.8574   1.0000
   3.750   0.9098   0.02252   0.01550  -0.1411   0.8471   1.0000
   4.000   0.9652   0.02119   0.01441  -0.1444   0.8374   1.0000
   4.250   1.0119   0.01998   0.01344  -0.1459   0.8236   1.0000
   4.500   1.0486   0.01904   0.01272  -0.1458   0.8045   1.0000
   4.750   1.0919   0.01776   0.01173  -0.1463   0.7830   1.0000
   5.000   1.1242   0.01695   0.01113  -0.1451   0.7519   1.0000
   5.250   1.1525   0.01641   0.01072  -0.1434   0.7083   1.0000
   5.500   1.1786   0.01615   0.01042  -0.1412   0.6423   1.0000
   5.750   1.1982   0.01658   0.01048  -0.1381   0.5342   1.0000
   6.000   1.2052   0.01813   0.01112  -0.1336   0.3953   1.0000
   6.250   1.2082   0.02017   0.01223  -0.1295   0.2629   1.0000
   6.500   1.2127   0.02258   0.01367  -0.1261   0.1412   1.0000
   6.750   1.2131   0.02622   0.01652  -0.1214   0.0624   1.0000
   7.000   1.2245   0.02860   0.01888  -0.1184   0.0495   1.0000
   7.250   1.2414   0.03105   0.02132  -0.1164   0.0426   1.0000
   7.500   1.2629   0.03302   0.02339  -0.1152   0.0371   1.0000
   7.750   1.2929   0.03665   0.02704  -0.1154   0.0346   1.0000
   8.000   1.3251   0.04139   0.03212  -0.1156   0.0338   1.0000
   8.250   1.3480   0.04550   0.03667  -0.1144   0.0338   1.0000
   8.500   1.3663   0.04956   0.04122  -0.1127   0.0341   1.0000
   8.750   1.3804   0.05224   0.04442  -0.1100   0.0349   1.0000
   9.000   1.3820   0.05701   0.05016  -0.1052   0.0377   1.0000
   9.250   1.3779   0.06278   0.05658  -0.1012   0.0403   1.0000
   9.500   1.3733   0.06820   0.06239  -0.0980   0.0423   1.0000
   9.750   1.3717   0.07505   0.06940  -0.0962   0.0445   1.0000
  10.000   1.2877   0.07488   0.06987  -0.0831   0.0459   1.0000
  10.250   1.2550   0.07790   0.07323  -0.0777   0.0466   1.0000
  10.500   1.2236   0.08232   0.07792  -0.0746   0.0468   1.0000
  10.750   1.1919   0.08762   0.08347  -0.0730   0.0469   1.0000
  11.000   1.1608   0.09334   0.08939  -0.0728   0.0469   1.0000
  11.250   1.1307   0.09933   0.09557  -0.0739   0.0468   1.0000
  11.500   1.0995   0.10549   0.10188  -0.0760   0.0466   1.0000
  11.750   1.0677   0.11165   0.10817  -0.0790   0.0464   1.0000
  12.000   1.0367   0.11904   0.11568  -0.0840   0.0463   1.0000
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