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E471 (6.25%) (e471-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E471 (6.25%) (e471-il)
Reynolds number: 1,000,000
Max Cl/Cd: 189.49 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e471-il-1000000.txt
Download as CSV file: xf-e471-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2813   0.09297   0.09136  -0.0502   0.9902   0.0069
  -8.000  -0.2669   0.08885   0.08724  -0.0543   0.9881   0.0070
  -7.750  -0.2576   0.08388   0.08228  -0.0578   0.9864   0.0075
  -7.500  -0.2397   0.08063   0.07903  -0.0618   0.9850   0.0077
  -7.250  -0.2199   0.07742   0.07581  -0.0665   0.9836   0.0083
  -7.000  -0.2092   0.07439   0.07279  -0.0691   0.9780   0.0087
  -6.750  -0.1863   0.07004   0.06844  -0.0757   0.9747   0.0093
  -6.500  -0.1529   0.06540   0.06378  -0.0854   0.9727   0.0108
  -6.250  -0.1195   0.06063   0.05900  -0.0946   0.9714   0.0110
  -6.000  -0.0902   0.05573   0.05408  -0.1030   0.9677   0.0111
  -5.750  -0.0588   0.05039   0.04868  -0.1119   0.9630   0.0111
  -5.500  -0.0151   0.04354   0.04175  -0.1243   0.9611   0.0112
  -5.250   0.0356   0.03493   0.03295  -0.1377   0.9598   0.0112
  -5.000   0.0874   0.02228   0.01966  -0.1532   0.9580   0.0126
  -4.750   0.1145   0.02073   0.01797  -0.1545   0.9537   0.0133
  -4.500   0.1460   0.01863   0.01565  -0.1565   0.9502   0.0145
  -4.250   0.1792   0.01741   0.01425  -0.1580   0.9477   0.0171
  -4.000   0.2123   0.01724   0.01393  -0.1588   0.9456   0.0182
  -3.750   0.2448   0.01521   0.01158  -0.1604   0.9419   0.0183
  -3.250   0.3109   0.00964   0.00529  -0.1635   0.9337   0.0173
  -3.000   0.3429   0.00867   0.00418  -0.1644   0.9300   0.0172
  -2.750   0.3713   0.00805   0.00349  -0.1645   0.9239   0.0173
  -2.500   0.4026   0.00744   0.00278  -0.1653   0.9193   0.0173
  -2.250   0.4321   0.00693   0.00217  -0.1656   0.9128   0.0169
  -2.000   0.4623   0.00657   0.00171  -0.1660   0.9062   0.0169
  -1.750   0.4910   0.00634   0.00140  -0.1661   0.8986   0.0173
  -1.500   0.5204   0.00619   0.00115  -0.1663   0.8912   0.0183
  -1.250   0.5482   0.00607   0.00095  -0.1661   0.8825   0.0212
  -1.000   0.5764   0.00601   0.00086  -0.1661   0.8746   0.0267
  -0.750   0.6053   0.00566   0.00082  -0.1665   0.8659   0.1471
  -0.500   0.6338   0.00536   0.00085  -0.1669   0.8569   0.2851
  -0.250   0.6621   0.00518   0.00088  -0.1672   0.8483   0.3906
   0.000   0.6901   0.00498   0.00093  -0.1673   0.8388   0.5077
   0.250   0.7181   0.00466   0.00105  -0.1675   0.8289   0.6964
   0.500   0.7350   0.00415   0.00111  -0.1647   0.8185   1.0000
   0.750   0.7624   0.00423   0.00113  -0.1646   0.8079   1.0000
   1.000   0.7896   0.00431   0.00115  -0.1644   0.7966   1.0000
   1.250   0.8167   0.00440   0.00118  -0.1642   0.7843   1.0000
   1.500   0.8435   0.00449   0.00122  -0.1639   0.7704   1.0000
   1.750   0.8700   0.00461   0.00129  -0.1635   0.7548   1.0000
   2.000   0.8963   0.00473   0.00135  -0.1632   0.7368   1.0000
   2.250   0.9220   0.00489   0.00143  -0.1627   0.7151   1.0000
   2.500   0.9473   0.00508   0.00152  -0.1621   0.6889   1.0000
   2.750   0.9719   0.00532   0.00164  -0.1614   0.6582   1.0000
   3.000   0.9950   0.00567   0.00182  -0.1604   0.6106   1.0000
   3.250   1.0146   0.00632   0.00208  -0.1588   0.5268   1.0000
   3.500   1.0331   0.00718   0.00245  -0.1572   0.4256   1.0000
   3.750   1.0538   0.00791   0.00280  -0.1560   0.3456   1.0000
   4.000   1.0744   0.00867   0.00318  -0.1548   0.2681   1.0000
   4.250   1.0944   0.00952   0.00363  -0.1536   0.1880   1.0000
   4.500   1.1156   0.01026   0.00405  -0.1525   0.1260   1.0000
   4.750   1.1367   0.01101   0.00450  -0.1514   0.0731   1.0000
   5.000   1.1555   0.01210   0.00520  -0.1499   0.0125   1.0000
   5.250   1.1790   0.01262   0.00572  -0.1490   0.0070   1.0000
   5.500   1.2028   0.01310   0.00628  -0.1482   0.0062   1.0000
   5.750   1.2256   0.01373   0.00704  -0.1471   0.0058   1.0000
   6.000   1.2482   0.01434   0.00773  -0.1461   0.0054   1.0000
   6.250   1.2709   0.01492   0.00837  -0.1452   0.0053   1.0000
   6.500   1.2927   0.01563   0.00916  -0.1440   0.0051   1.0000
   6.750   1.3138   0.01639   0.01001  -0.1428   0.0049   1.0000
   7.000   1.3342   0.01724   0.01095  -0.1414   0.0047   1.0000
   7.250   1.3541   0.01814   0.01196  -0.1400   0.0045   1.0000
   7.500   1.3735   0.01913   0.01302  -0.1385   0.0041   1.0000
   7.750   1.3920   0.02024   0.01423  -0.1369   0.0039   1.0000
   8.000   1.4093   0.02161   0.01570  -0.1352   0.0037   1.0000
   8.250   1.4260   0.02330   0.01754  -0.1332   0.0036   1.0000
   8.500   1.4416   0.02682   0.02144  -0.1306   0.0041   1.0000
   8.750   1.4556   0.03532   0.03075  -0.1265   0.0072   1.0000
   9.000   1.4677   0.03754   0.03317  -0.1243   0.0068   1.0000
   9.250   1.4779   0.03979   0.03560  -0.1219   0.0066   1.0000
   9.500   1.4858   0.04218   0.03818  -0.1194   0.0064   1.0000
   9.750   1.4887   0.04496   0.04117  -0.1163   0.0062   1.0000
  10.000   1.4857   0.04823   0.04466  -0.1127   0.0060   1.0000
  10.250   1.4692   0.05219   0.04886  -0.1073   0.0059   1.0000
  10.500   1.4449   0.05645   0.05336  -0.1016   0.0058   1.0000
  10.750   1.4131   0.06194   0.05913  -0.0965   0.0057   1.0000
  11.000   1.3577   0.07121   0.06874  -0.0924   0.0056   1.0000
  11.250   1.3379   0.07608   0.07379  -0.0914   0.0056   1.0000
  11.500   1.3170   0.08164   0.07951  -0.0916   0.0056   1.0000
  11.750   1.2969   0.08774   0.08576  -0.0931   0.0056   1.0000
  12.000   1.2156   0.08781   0.08601  -0.0855   0.0062   1.0000
  12.250   1.1727   0.09651   0.09493  -0.0888   0.0063   1.0000
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