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E71 (5.15%) (e71-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E71 (5.15%) (e71-il)
Reynolds number: 500,000
Max Cl/Cd: 143.58 at α=1.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e71-il-500000-n5.txt
Download as CSV file: xf-e71-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E71  (5.15%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3286   0.09736   0.09509  -0.0351   0.9933   0.0066
  -7.750  -0.3205   0.09324   0.09097  -0.0371   0.9912   0.0064
  -7.500  -0.3101   0.08946   0.08721  -0.0400   0.9886   0.0063
  -7.250  -0.2982   0.08573   0.08348  -0.0432   0.9860   0.0062
  -7.000  -0.2837   0.08193   0.07969  -0.0474   0.9836   0.0061
  -6.750  -0.2670   0.07744   0.07521  -0.0527   0.9795   0.0064
  -6.500  -0.2459   0.07294   0.07073  -0.0594   0.9748   0.0068
  -6.250  -0.2285   0.06853   0.06631  -0.0649   0.9723   0.0076
  -6.000  -0.2023   0.06504   0.06281  -0.0709   0.9706   0.0082
  -5.750  -0.1823   0.06126   0.05902  -0.0760   0.9656   0.0086
  -5.500  -0.1469   0.05840   0.05613  -0.0833   0.9621   0.0129
  -5.250  -0.1102   0.05301   0.05069  -0.0929   0.9597   0.0130
  -5.000  -0.0695   0.04561   0.04319  -0.1054   0.9581   0.0110
  -4.750  -0.0229   0.03856   0.03597  -0.1172   0.9553   0.0105
  -4.500   0.0259   0.03112   0.02825  -0.1277   0.9519   0.0107
  -4.250   0.0766   0.02465   0.02134  -0.1361   0.9508   0.0115
  -4.000   0.1193   0.02088   0.01718  -0.1409   0.9498   0.0122
  -3.500   0.1985   0.01588   0.01137  -0.1477   0.9479   0.0125
  -3.250   0.2368   0.01388   0.00898  -0.1504   0.9471   0.0121
  -3.000   0.2734   0.01243   0.00725  -0.1525   0.9462   0.0118
  -2.750   0.3091   0.01134   0.00596  -0.1542   0.9453   0.0117
  -2.500   0.3399   0.01053   0.00501  -0.1549   0.9422   0.0115
  -2.250   0.3699   0.00988   0.00425  -0.1553   0.9383   0.0116
  -2.000   0.4033   0.00928   0.00357  -0.1565   0.9358   0.0117
  -1.750   0.4380   0.00878   0.00300  -0.1579   0.9335   0.0121
  -1.500   0.4712   0.00842   0.00259  -0.1590   0.9298   0.0130
  -1.250   0.5020   0.00812   0.00223  -0.1596   0.9235   0.0148
  -1.000   0.5395   0.00785   0.00189  -0.1615   0.9197   0.0168
  -0.750   0.5723   0.00766   0.00169  -0.1625   0.9127   0.0211
  -0.500   0.6103   0.00739   0.00148  -0.1647   0.9063   0.0464
  -0.250   0.6459   0.00711   0.00134  -0.1664   0.8959   0.1114
   0.000   0.6827   0.00671   0.00130  -0.1686   0.8839   0.2589
   0.250   0.7182   0.00633   0.00132  -0.1705   0.8685   0.4362
   0.500   0.7489   0.00563   0.00152  -0.1712   0.8483   0.8031
   1.000   0.7948   0.00554   0.00147  -0.1683   0.8015   1.0000
   1.250   0.8213   0.00572   0.00152  -0.1679   0.7739   1.0000
   1.500   0.8465   0.00596   0.00159  -0.1672   0.7392   1.0000
   1.750   0.8705   0.00627   0.00170  -0.1662   0.6983   1.0000
   2.000   0.8937   0.00663   0.00188  -0.1652   0.6522   1.0000
   2.250   0.9160   0.00707   0.00207  -0.1640   0.5970   1.0000
   2.500   0.9376   0.00762   0.00230  -0.1627   0.5308   1.0000
   2.750   0.9581   0.00834   0.00261  -0.1613   0.4474   1.0000
   3.000   0.9739   0.00975   0.00314  -0.1594   0.2813   1.0000
   3.250   0.9942   0.01076   0.00359  -0.1583   0.1754   1.0000
   3.500   1.0165   0.01153   0.00399  -0.1574   0.1073   1.0000
   3.750   1.0397   0.01221   0.00445  -0.1567   0.0595   1.0000
   4.000   1.0633   0.01282   0.00490  -0.1560   0.0269   1.0000
   4.250   1.0869   0.01346   0.00543  -0.1552   0.0073   1.0000
   4.500   1.1120   0.01386   0.00588  -0.1546   0.0060   1.0000
   4.750   1.1368   0.01431   0.00643  -0.1539   0.0051   1.0000
   5.000   1.1611   0.01485   0.00708  -0.1531   0.0046   1.0000
   5.250   1.1847   0.01551   0.00786  -0.1522   0.0044   1.0000
   5.500   1.2075   0.01629   0.00875  -0.1511   0.0042   1.0000
   5.750   1.2297   0.01716   0.00981  -0.1500   0.0041   1.0000
   6.000   1.2508   0.01821   0.01098  -0.1486   0.0040   1.0000
   6.250   1.2686   0.01993   0.01289  -0.1466   0.0036   1.0000
   6.500   1.2892   0.02122   0.01432  -0.1453   0.0032   1.0000
   6.750   1.3112   0.02217   0.01538  -0.1442   0.0030   1.0000
   7.000   1.3321   0.02351   0.01688  -0.1429   0.0029   1.0000
   7.250   1.3526   0.02502   0.01858  -0.1415   0.0027   1.0000
   7.500   1.3726   0.02674   0.02050  -0.1401   0.0025   1.0000
   7.750   1.3917   0.02873   0.02275  -0.1385   0.0023   1.0000
   8.000   1.4090   0.03110   0.02546  -0.1366   0.0022   1.0000
   8.250   1.4242   0.03376   0.02845  -0.1345   0.0021   1.0000
   8.500   1.4364   0.03680   0.03185  -0.1320   0.0020   1.0000
   8.750   1.4444   0.04036   0.03581  -0.1290   0.0020   1.0000
   9.000   1.4477   0.04427   0.04013  -0.1256   0.0020   1.0000
   9.250   1.4446   0.04869   0.04496  -0.1215   0.0020   1.0000
   9.500   1.4355   0.05323   0.04986  -0.1171   0.0020   1.0000
   9.750   1.4181   0.05717   0.05408  -0.1117   0.0021   1.0000
  10.000   1.3978   0.06145   0.05862  -0.1070   0.0021   1.0000
  10.250   1.3764   0.06622   0.06363  -0.1036   0.0021   1.0000
  10.500   1.3550   0.07140   0.06902  -0.1017   0.0021   1.0000
  10.750   1.3321   0.07743   0.07525  -0.1016   0.0021   1.0000
  11.000   1.3096   0.08422   0.08223  -0.1033   0.0021   1.0000
  11.250   1.2876   0.09219   0.09036  -0.1074   0.0022   1.0000
  11.500   1.2662   0.10210   0.10043  -0.1142   0.0022   1.0000
  11.750   1.2441   0.11659   0.11507  -0.1249   0.0022   1.0000
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