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E71 (5.15%) (e71-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E71 (5.15%) (e71-il)
Reynolds number: 50,000
Max Cl/Cd: 48.52 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e71-il-50000.txt
Download as CSV file: xf-e71-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3735   0.11241   0.10563  -0.0229   1.0000   0.1274
  -7.750  -0.3815   0.11187   0.10521  -0.0227   1.0000   0.1308
  -7.500  -0.3962   0.11230   0.10579  -0.0221   1.0000   0.1319
  -7.250  -0.3752   0.10556   0.09903  -0.0205   1.0000   0.1395
  -7.000  -0.3850   0.10485   0.09844  -0.0194   1.0000   0.1440
  -6.750  -0.3956   0.10489   0.09864  -0.0211   1.0000   0.1457
  -6.500  -0.3826   0.09936   0.09311  -0.0173   1.0000   0.1549
  -6.250  -0.3898   0.09895   0.09283  -0.0202   1.0000   0.1593
  -6.000  -0.3814   0.09442   0.08833  -0.0167   1.0000   0.1654
  -5.750  -0.3830   0.09345   0.08747  -0.0208   1.0000   0.1732
  -5.500  -0.3766   0.08921   0.08322  -0.0170   1.0000   0.1793
  -5.250  -0.3718   0.08769   0.08177  -0.0233   1.0000   0.1881
  -5.000  -0.3665   0.08379   0.07791  -0.0181   1.0000   0.1963
  -4.750  -0.3594   0.08084   0.07501  -0.0197   1.0000   0.2055
  -4.500  -0.3495   0.07796   0.07217  -0.0221   1.0000   0.2178
  -4.250  -0.3388   0.07494   0.06917  -0.0232   1.0000   0.2316
  -4.000  -0.3282   0.07183   0.06610  -0.0233   1.0000   0.2467
  -3.750  -0.3163   0.06884   0.06313  -0.0234   1.0000   0.2642
  -3.500  -0.3005   0.06575   0.06006  -0.0255   1.0000   0.2876
  -3.250  -0.2847   0.06285   0.05716  -0.0266   1.0000   0.3142
  -3.000  -0.2723   0.06000   0.05435  -0.0256   1.0000   0.3426
  -2.750  -0.2591   0.05741   0.05178  -0.0247   1.0000   0.3826
  -2.500  -0.2555   0.05500   0.04940  -0.0196   1.0000   0.4252
  -2.250   0.0321   0.03650   0.02815  -0.0972   1.0000   0.1463
  -2.000   0.0848   0.03246   0.02351  -0.1029   1.0000   0.1281
  -1.750   0.1384   0.02946   0.01943  -0.1080   1.0000   0.1184
  -1.500   0.1758   0.02750   0.01701  -0.1098   1.0000   0.1182
  -1.250   0.2094   0.02592   0.01516  -0.1110   1.0000   0.1224
  -1.000   0.2404   0.02492   0.01399  -0.1115   1.0000   0.1386
  -0.750   0.2711   0.02394   0.01290  -0.1118   1.0000   0.1680
  -0.500   0.2978   0.01981   0.01160  -0.1098   1.0000   0.9158
  -0.250   0.3233   0.02012   0.01104  -0.1095   1.0000   1.0000
   0.000   0.3484   0.02053   0.01100  -0.1095   1.0000   1.0000
   0.250   0.3725   0.02098   0.01108  -0.1093   1.0000   1.0000
   0.500   0.3961   0.02146   0.01131  -0.1092   1.0000   1.0000
   0.750   0.4190   0.02199   0.01163  -0.1090   1.0000   1.0000
   1.000   0.4415   0.02256   0.01204  -0.1088   1.0000   1.0000
   1.250   0.4634   0.02317   0.01253  -0.1086   1.0000   1.0000
   1.500   0.4850   0.02383   0.01310  -0.1084   1.0000   1.0000
   1.750   0.5059   0.02454   0.01375  -0.1082   1.0000   1.0000
   2.000   0.5262   0.02532   0.01449  -0.1080   1.0000   1.0000
   2.250   0.5460   0.02616   0.01532  -0.1078   1.0000   1.0000
   2.500   0.5652   0.02707   0.01625  -0.1076   1.0000   1.0000
   2.750   0.5838   0.02807   0.01729  -0.1075   1.0000   1.0000
   3.000   0.6017   0.02916   0.01848  -0.1074   1.0000   1.0000
   3.250   0.6188   0.03036   0.01976  -0.1074   1.0000   1.0000
   3.500   0.6351   0.03168   0.02117  -0.1074   1.0000   1.0000
   3.750   0.6720   0.03334   0.02301  -0.1115   0.9868   1.0000
   4.000   0.7344   0.03471   0.02474  -0.1193   0.9593   1.0000
   4.250   0.7941   0.03538   0.02575  -0.1257   0.9298   1.0000
   4.500   0.8533   0.03542   0.02618  -0.1309   0.8979   1.0000
   4.750   0.9254   0.03435   0.02577  -0.1366   0.8649   1.0000
   5.000   0.9987   0.03186   0.02398  -0.1401   0.8256   1.0000
   5.250   1.0783   0.02740   0.02039  -0.1413   0.7734   1.0000
   5.500   1.1375   0.02356   0.01714  -0.1380   0.6721   1.0000
   5.750   1.1596   0.02390   0.01640  -0.1315   0.4733   1.0000
   6.000   1.1621   0.02727   0.01822  -0.1260   0.3048   1.0000
   6.250   1.1693   0.03139   0.02109  -0.1222   0.1715   1.0000
   6.500   1.1914   0.03535   0.02445  -0.1205   0.1059   1.0000
   6.750   1.2225   0.03894   0.02797  -0.1201   0.0845   1.0000
   7.000   1.2548   0.04291   0.03203  -0.1200   0.0755   1.0000
   7.250   1.2818   0.04728   0.03699  -0.1187   0.0732   1.0000
   7.500   1.3024   0.05178   0.04225  -0.1167   0.0726   1.0000
   7.750   1.3182   0.05665   0.04770  -0.1145   0.0731   1.0000
   8.000   1.3313   0.06192   0.05343  -0.1124   0.0741   1.0000
   8.250   1.3426   0.06777   0.05962  -0.1106   0.0749   1.0000
   8.500   1.3279   0.07222   0.06534  -0.1054   0.0798   1.0000
   8.750   1.3200   0.07800   0.07161  -0.1027   0.0828   1.0000
   9.000   1.3139   0.08360   0.07750  -0.1006   0.0850   1.0000
   9.250   1.3160   0.08976   0.08377  -0.0995   0.0870   1.0000
   9.500   1.1984   0.09050   0.08525  -0.0851   0.0884   1.0000
   9.750   1.1538   0.09534   0.09035  -0.0829   0.0892   1.0000
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