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E71 (5.15%) (e71-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E71 (5.15%) (e71-il)
Reynolds number: 1,000,000
Max Cl/Cd: 204.95 at α=1°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e71-il-1000000.txt
Download as CSV file: xf-e71-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3257   0.09133   0.08977  -0.0343   0.9925   0.0064
  -7.250  -0.3129   0.08802   0.08646  -0.0375   0.9897   0.0067
  -7.000  -0.2983   0.08456   0.08301  -0.0413   0.9871   0.0072
  -6.750  -0.2791   0.08071   0.07915  -0.0466   0.9849   0.0073
  -6.500  -0.2460   0.07588   0.07431  -0.0559   0.9835   0.0086
  -6.250  -0.2288   0.07218   0.07062  -0.0605   0.9780   0.0088
  -6.000  -0.2020   0.06760   0.06602  -0.0678   0.9752   0.0089
  -5.000  -0.0397   0.03900   0.03715  -0.1171   0.9659   0.0096
  -4.750   0.0017   0.03404   0.03205  -0.1254   0.9640   0.0101
  -4.500   0.0448   0.02957   0.02741  -0.1327   0.9629   0.0107
  -4.250   0.0894   0.02518   0.02277  -0.1393   0.9622   0.0118
  -4.000   0.1292   0.02286   0.02027  -0.1424   0.9615   0.0148
  -2.250   0.4082   0.00830   0.00381  -0.1640   0.9587   0.0146
  -2.000   0.4459   0.00786   0.00333  -0.1661   0.9581   0.0155
  -1.750   0.4724   0.00714   0.00251  -0.1657   0.9523   0.0168
  -1.500   0.5067   0.00676   0.00207  -0.1670   0.9498   0.0174
  -1.250   0.5416   0.00644   0.00170  -0.1684   0.9473   0.0187
  -1.000   0.5758   0.00619   0.00141  -0.1696   0.9443   0.0190
  -0.750   0.6027   0.00603   0.00122  -0.1692   0.9364   0.0197
  -0.500   0.6395   0.00569   0.00102  -0.1712   0.9322   0.0754
  -0.250   0.6725   0.00513   0.00101  -0.1726   0.9225   0.2950
   0.000   0.7070   0.00473   0.00099  -0.1743   0.9116   0.4644
   0.250   0.7406   0.00421   0.00109  -0.1758   0.8991   0.7322
   0.500   0.7601   0.00377   0.00107  -0.1735   0.8827   1.0000
   0.750   0.7886   0.00386   0.00107  -0.1735   0.8637   1.0000
   1.000   0.8157   0.00398   0.00109  -0.1731   0.8410   1.0000
   1.250   0.8419   0.00413   0.00113  -0.1727   0.8170   1.0000
   1.500   0.8675   0.00431   0.00119  -0.1720   0.7900   1.0000
   1.750   0.8920   0.00455   0.00128  -0.1712   0.7561   1.0000
   2.000   0.9157   0.00484   0.00141  -0.1702   0.7153   1.0000
   2.250   0.9389   0.00518   0.00155  -0.1691   0.6674   1.0000
   2.500   0.9612   0.00563   0.00173  -0.1679   0.6076   1.0000
   2.750   0.9790   0.00658   0.00207  -0.1660   0.4804   1.0000
   3.000   0.9990   0.00746   0.00242  -0.1646   0.3681   1.0000
   3.250   1.0210   0.00820   0.00275  -0.1637   0.2833   1.0000
   3.500   1.0429   0.00896   0.00314  -0.1627   0.2014   1.0000
   3.750   1.0640   0.00989   0.00359  -0.1617   0.1124   1.0000
   4.000   1.0858   0.01075   0.00407  -0.1607   0.0436   1.0000
   4.250   1.1084   0.01158   0.00467  -0.1596   0.0075   1.0000
   4.500   1.1334   0.01206   0.00528  -0.1589   0.0059   1.0000
   4.750   1.1582   0.01254   0.00585  -0.1581   0.0057   1.0000
   5.000   1.1823   0.01314   0.00655  -0.1573   0.0056   1.0000
   5.250   1.2055   0.01388   0.00741  -0.1562   0.0056   1.0000
   5.500   1.2275   0.01485   0.00850  -0.1549   0.0057   1.0000
   5.750   1.2489   0.01589   0.00965  -0.1535   0.0057   1.0000
   6.000   1.2717   0.01668   0.01051  -0.1525   0.0054   1.0000
   6.250   1.2936   0.01766   0.01159  -0.1513   0.0052   1.0000
   6.500   1.3145   0.01898   0.01305  -0.1498   0.0052   1.0000
   6.750   1.3358   0.02039   0.01459  -0.1484   0.0051   1.0000
   7.000   1.3571   0.02199   0.01634  -0.1471   0.0049   1.0000
   7.250   1.3784   0.02357   0.01808  -0.1457   0.0046   1.0000
   7.500   1.3979   0.02629   0.02107  -0.1438   0.0045   1.0000
   8.000   1.3613   0.03619   0.03261  -0.1279   0.0059   1.0000
   8.250   1.3636   0.04052   0.03724  -0.1245   0.0059   1.0000
   8.500   1.4340   0.04464   0.04115  -0.1306   0.0053   1.0000
   8.750   1.4421   0.04772   0.04449  -0.1278   0.0049   1.0000
   9.000   1.4421   0.05182   0.04892  -0.1242   0.0048   1.0000
   9.250   1.4371   0.05615   0.05353  -0.1203   0.0046   1.0000
   9.500   1.4256   0.06059   0.05822  -0.1161   0.0045   1.0000
   9.750   1.4059   0.06414   0.06195  -0.1107   0.0044   1.0000
  10.000   1.3841   0.06828   0.06628  -0.1065   0.0045   1.0000
  10.250   1.3617   0.07304   0.07121  -0.1037   0.0044   1.0000
  10.500   1.3372   0.07872   0.07706  -0.1027   0.0045   1.0000
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