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E71 (5.15%) (e71-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E71 (5.15%) (e71-il)
Reynolds number: 100,000
Max Cl/Cd: 75.06 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e71-il-100000.txt
Download as CSV file: xf-e71-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3773   0.09922   0.09463  -0.0195   1.0000   0.0597
  -6.750  -0.3841   0.09782   0.09331  -0.0181   1.0000   0.0609
  -6.500  -0.3892   0.09663   0.09222  -0.0196   1.0000   0.0625
  -6.250  -0.3871   0.09548   0.09115  -0.0258   1.0000   0.0634
  -6.000  -0.3736   0.09321   0.08889  -0.0349   1.0000   0.0638
  -5.750  -0.3822   0.08757   0.08333  -0.0221   1.0000   0.0657
  -5.500  -0.3782   0.08466   0.08045  -0.0199   1.0000   0.0681
  -5.250  -0.3717   0.08185   0.07767  -0.0209   1.0000   0.0710
  -5.000  -0.3572   0.07880   0.07459  -0.0265   1.0000   0.0752
  -4.750  -0.3265   0.07403   0.06977  -0.0395   1.0000   0.0781
  -4.500  -0.3271   0.07113   0.06692  -0.0341   1.0000   0.0801
  -4.250  -0.2622   0.06633   0.06179  -0.0560   1.0000   0.0910
  -4.000  -0.2691   0.06266   0.05831  -0.0488   1.0000   0.0925
  -3.750  -0.2452   0.05972   0.05531  -0.0519   1.0000   0.1033
  -3.500  -0.2291   0.05614   0.05175  -0.0526   1.0000   0.1096
  -3.250  -0.1894   0.05188   0.04735  -0.0604   1.0000   0.1220
  -3.000  -0.1525   0.04817   0.04351  -0.0663   1.0000   0.1362
  -2.750  -0.1013   0.04437   0.03939  -0.0757   1.0000   0.1612
  -2.500  -0.0736   0.04155   0.03655  -0.0776   1.0000   0.1770
  -2.250  -0.0362   0.03887   0.03374  -0.0819   1.0000   0.2042
  -2.000   0.1096   0.02646   0.01912  -0.1062   1.0000   0.0711
  -1.750   0.1534   0.02413   0.01616  -0.1094   1.0000   0.0688
  -1.500   0.1900   0.02262   0.01424  -0.1111   1.0000   0.0698
  -1.250   0.2246   0.02135   0.01258  -0.1122   1.0000   0.0689
  -1.000   0.2557   0.02049   0.01161  -0.1128   1.0000   0.0706
  -0.750   0.2859   0.01989   0.01094  -0.1134   1.0000   0.0753
  -0.500   0.3178   0.01937   0.01043  -0.1144   1.0000   0.0892
  -0.250   0.3510   0.01660   0.01020  -0.1148   1.0000   0.9059
   0.000   0.3711   0.01699   0.01027  -0.1140   1.0000   1.0000
   0.250   0.3942   0.01748   0.01052  -0.1137   1.0000   1.0000
   0.500   0.4166   0.01801   0.01086  -0.1134   1.0000   1.0000
   0.750   0.4385   0.01858   0.01130  -0.1131   1.0000   1.0000
   1.000   0.4599   0.01919   0.01181  -0.1128   1.0000   1.0000
   1.250   0.4894   0.01989   0.01242  -0.1142   0.9962   1.0000
   1.500   0.5345   0.02057   0.01301  -0.1183   0.9857   1.0000
   1.750   0.5782   0.02110   0.01350  -0.1220   0.9745   1.0000
   2.000   0.6216   0.02148   0.01389  -0.1255   0.9629   1.0000
   2.250   0.6654   0.02172   0.01418  -0.1288   0.9509   1.0000
   2.500   0.7094   0.02182   0.01433  -0.1320   0.9386   1.0000
   2.750   0.7542   0.02173   0.01434  -0.1351   0.9256   1.0000
   3.000   0.8002   0.02144   0.01418  -0.1381   0.9119   1.0000
   3.250   0.8466   0.02096   0.01393  -0.1408   0.8979   1.0000
   3.500   0.8945   0.02022   0.01341  -0.1435   0.8834   1.0000
   3.750   0.9453   0.01909   0.01254  -0.1461   0.8684   1.0000
   4.000   1.0007   0.01760   0.01143  -0.1491   0.8516   1.0000
   4.250   1.0458   0.01638   0.01050  -0.1500   0.8245   1.0000
   4.500   1.0854   0.01548   0.00982  -0.1500   0.7821   1.0000
   4.750   1.1224   0.01498   0.00938  -0.1495   0.7128   1.0000
   5.000   1.1499   0.01532   0.00934  -0.1474   0.5858   1.0000
   5.250   1.1579   0.01712   0.00989  -0.1428   0.3954   1.0000
   5.500   1.1640   0.01944   0.01099  -0.1392   0.2241   1.0000
   5.750   1.1677   0.02333   0.01352  -0.1352   0.0681   1.0000
   6.000   1.1802   0.02605   0.01609  -0.1320   0.0496   1.0000
   6.250   1.2003   0.02806   0.01824  -0.1300   0.0430   1.0000
   6.500   1.2220   0.03084   0.02097  -0.1289   0.0374   1.0000
   6.750   1.2486   0.03315   0.02355  -0.1279   0.0345   1.0000
   7.000   1.2766   0.03637   0.02717  -0.1271   0.0336   1.0000
   7.250   1.3017   0.04011   0.03137  -0.1257   0.0338   1.0000
   7.500   1.3217   0.04429   0.03611  -0.1237   0.0347   1.0000
   7.750   1.3369   0.04894   0.04130  -0.1213   0.0359   1.0000
   8.000   1.3476   0.05428   0.04709  -0.1190   0.0372   1.0000
   8.250   1.3571   0.05868   0.05230  -0.1151   0.0414   1.0000
   8.500   1.3530   0.06590   0.06021  -0.1111   0.0467   1.0000
   8.750   1.3523   0.07574   0.07054  -0.1083   0.0611   1.0000
   9.000   1.2635   0.07708   0.07265  -0.0954   0.0612   1.0000
   9.250   1.2268   0.08051   0.07644  -0.0900   0.0599   1.0000
   9.500   1.1975   0.08513   0.08126  -0.0868   0.0597   1.0000
   9.750   1.1696   0.09081   0.08711  -0.0854   0.0601   1.0000
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