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E474 (14.09%) (e474-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E474 (14.09%) (e474-il)
Reynolds number: 50,000
Max Cl/Cd: 22.93 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e474-il-50000-n5.txt
Download as CSV file: xf-e474-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E474  (14.09%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6577   0.09675   0.08782  -0.0134   1.0000   0.1707
 -11.250  -0.6547   0.09365   0.08469  -0.0140   1.0000   0.1749
 -11.000  -0.7671   0.07194   0.06308  -0.0282   1.0000   0.1829
 -10.750  -0.7201   0.07590   0.06701  -0.0235   1.0000   0.1853
 -10.500  -0.7528   0.06811   0.05921  -0.0275   1.0000   0.1902
 -10.250  -0.8527   0.05699   0.04796  -0.0280   1.0000   0.1932
 -10.000  -0.9078   0.05093   0.04153  -0.0241   1.0000   0.1968
  -9.750  -0.8861   0.05040   0.04102  -0.0230   1.0000   0.2004
  -9.500  -0.8763   0.04903   0.03958  -0.0213   1.0000   0.2044
  -9.250  -0.8815   0.04652   0.03683  -0.0188   1.0000   0.2092
  -9.000  -0.8863   0.04395   0.03395  -0.0160   1.0000   0.2139
  -8.750  -0.8656   0.04333   0.03337  -0.0148   1.0000   0.2178
  -8.500  -0.8552   0.04191   0.03180  -0.0129   1.0000   0.2225
  -8.250  -0.8547   0.03974   0.02923  -0.0101   1.0000   0.2282
  -8.000  -0.8355   0.03891   0.02843  -0.0088   1.0000   0.2322
  -7.750  -0.8190   0.03798   0.02744  -0.0072   1.0000   0.2369
  -7.500  -0.8086   0.03650   0.02570  -0.0051   1.0000   0.2424
  -7.250  -0.7936   0.03533   0.02439  -0.0034   1.0000   0.2472
  -7.000  -0.7742   0.03459   0.02365  -0.0020   1.0000   0.2519
  -6.750  -0.7590   0.03351   0.02240  -0.0003   1.0000   0.2577
  -6.500  -0.7432   0.03242   0.02113   0.0013   1.0000   0.2630
  -6.250  -0.7227   0.03173   0.02046   0.0026   1.0000   0.2676
  -6.000  -0.7049   0.03087   0.01948   0.0041   1.0000   0.2736
  -5.750  -0.6873   0.02997   0.01843   0.0057   1.0000   0.2795
  -5.500  -0.6665   0.02933   0.01784   0.0069   1.0000   0.2844
  -5.250  -0.6474   0.02859   0.01698   0.0083   1.0000   0.2906
  -5.000  -0.6279   0.02787   0.01618   0.0096   1.0000   0.2967
  -4.750  -0.6071   0.02730   0.01565   0.0108   1.0000   0.3025
  -4.500  -0.5873   0.02666   0.01488   0.0121   1.0000   0.3094
  -4.250  -0.5662   0.02610   0.01436   0.0133   1.0000   0.3153
  -4.000  -0.5454   0.02559   0.01386   0.0145   1.0000   0.3222
  -3.750  -0.5248   0.02507   0.01328   0.0156   1.0000   0.3297
  -3.500  -0.5035   0.02463   0.01292   0.0168   1.0000   0.3365
  -3.250  -0.4827   0.02419   0.01241   0.0178   1.0000   0.3450
  -3.000  -0.4613   0.02380   0.01216   0.0189   1.0000   0.3523
  -2.500  -0.4192   0.02313   0.01160   0.0210   1.0000   0.3703
  -2.250  -0.3983   0.02285   0.01136   0.0219   1.0000   0.3805
  -2.000  -0.3565   0.02263   0.01124   0.0189   0.9888   0.3947
  -1.750  -0.2990   0.02236   0.01113   0.0130   0.9677   0.4134
  -1.500  -0.2493   0.02195   0.01092   0.0090   0.9428   0.4329
  -1.250  -0.2037   0.02147   0.01066   0.0060   0.9147   0.4558
  -1.000  -0.1636   0.02096   0.01037   0.0042   0.8804   0.4823
  -0.750  -0.1238   0.02040   0.01006   0.0028   0.8400   0.5143
  -0.500  -0.0809   0.01982   0.00974   0.0012   0.7908   0.5554
  -0.250  -0.0377   0.01936   0.00944   0.0000   0.7313   0.6073
   0.000   0.0000   0.01919   0.00931   0.0000   0.6677   0.6676
   0.250   0.0377   0.01936   0.00945   0.0000   0.6073   0.7313
   0.500   0.0810   0.01983   0.00975  -0.0012   0.5552   0.7909
   0.750   0.1238   0.02040   0.01007  -0.0028   0.5143   0.8400
   1.000   0.1636   0.02096   0.01037  -0.0042   0.4823   0.8805
   1.250   0.2038   0.02147   0.01066  -0.0060   0.4559   0.9147
   1.500   0.2493   0.02195   0.01091  -0.0090   0.4330   0.9428
   1.750   0.2989   0.02236   0.01113  -0.0130   0.4134   0.9677
   2.000   0.3565   0.02263   0.01123  -0.0189   0.3949   0.9888
   2.250   0.3982   0.02285   0.01136  -0.0219   0.3804   1.0000
   2.500   0.4191   0.02313   0.01160  -0.0210   0.3703   1.0000
   3.000   0.4612   0.02380   0.01216  -0.0189   0.3523   1.0000
   3.250   0.4826   0.02419   0.01240  -0.0178   0.3450   1.0000
   3.500   0.5035   0.02463   0.01292  -0.0167   0.3365   1.0000
   3.750   0.5247   0.02507   0.01328  -0.0156   0.3297   1.0000
   4.000   0.5454   0.02559   0.01386  -0.0145   0.3222   1.0000
   4.250   0.5662   0.02610   0.01436  -0.0133   0.3153   1.0000
   4.500   0.5872   0.02666   0.01488  -0.0121   0.3095   1.0000
   4.750   0.6070   0.02730   0.01565  -0.0108   0.3025   1.0000
   5.000   0.6278   0.02787   0.01617  -0.0096   0.2967   1.0000
   5.250   0.6473   0.02859   0.01698  -0.0083   0.2906   1.0000
   5.500   0.6665   0.02933   0.01783  -0.0069   0.2845   1.0000
   5.750   0.6872   0.02997   0.01843  -0.0056   0.2795   1.0000
   6.000   0.7049   0.03087   0.01948  -0.0041   0.2736   1.0000
   6.250   0.7227   0.03173   0.02046  -0.0026   0.2676   1.0000
   6.500   0.7431   0.03242   0.02112  -0.0013   0.2630   1.0000
   6.750   0.7590   0.03352   0.02240   0.0003   0.2577   1.0000
   7.000   0.7742   0.03459   0.02365   0.0020   0.2519   1.0000
   7.250   0.7936   0.03534   0.02439   0.0034   0.2472   1.0000
   7.500   0.8086   0.03650   0.02570   0.0051   0.2424   1.0000
   7.750   0.8190   0.03798   0.02744   0.0072   0.2369   1.0000
   8.000   0.8355   0.03892   0.02844   0.0088   0.2323   1.0000
   8.250   0.8546   0.03974   0.02923   0.0102   0.2281   1.0000
   8.500   0.8553   0.04191   0.03180   0.0129   0.2225   1.0000
   8.750   0.8655   0.04335   0.03339   0.0148   0.2179   1.0000
   9.000   0.8862   0.04396   0.03396   0.0160   0.2139   1.0000
   9.250   0.8817   0.04651   0.03681   0.0187   0.2092   1.0000
   9.500   0.8765   0.04903   0.03958   0.0213   0.2044   1.0000
   9.750   0.8866   0.05036   0.04098   0.0230   0.2004   1.0000
  10.000   0.9078   0.05095   0.04155   0.0241   0.1968   1.0000
  10.250   0.8533   0.05698   0.04795   0.0279   0.1932   1.0000
  10.500   0.7552   0.06786   0.05896   0.0275   0.1901   1.0000
  10.750   0.7247   0.07522   0.06633   0.0240   0.1853   1.0000
  11.000   0.7684   0.07185   0.06299   0.0282   0.1829   1.0000
  11.250   0.6559   0.09358   0.08463   0.0140   0.1748   1.0000
  11.500   0.6588   0.09671   0.08778   0.0133   0.1707   1.0000
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