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EPPLER E850 AIRFOIL (e850-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E850 AIRFOIL (e850-il)
Reynolds number: 50,000
Max Cl/Cd: 23.07 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e850-il-50000.txt
Download as CSV file: xf-e850-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E850 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -6.500  -0.4470   0.07075   0.06492  -0.0102   1.0000   0.3188
  -6.000  -0.5684   0.05847   0.05132  -0.0432   1.0000   0.1251
  -5.750  -0.5508   0.05217   0.04453  -0.0441   1.0000   0.1001
  -5.500  -0.5337   0.04797   0.04014  -0.0437   1.0000   0.0951
  -5.250  -0.5121   0.04382   0.03513  -0.0440   1.0000   0.0847
  -5.000  -0.4912   0.03999   0.03074  -0.0437   1.0000   0.0828
  -4.750  -0.4676   0.03653   0.02678  -0.0432   1.0000   0.0799
  -4.500  -0.4416   0.03339   0.02305  -0.0424   1.0000   0.0770
  -4.250  -0.4148   0.03080   0.01990  -0.0413   1.0000   0.0754
  -4.000  -0.3892   0.02844   0.01731  -0.0399   1.0000   0.0772
  -3.750  -0.3643   0.02646   0.01517  -0.0379   1.0000   0.0832
  -3.500  -0.3418   0.02453   0.01331  -0.0363   1.0000   0.1052
  -3.250  -0.3160   0.02128   0.01073  -0.0359   1.0000   0.1929
  -3.000  -0.3320   0.01982   0.01216  -0.0217   1.0000   0.7179
  -2.750  -0.3478   0.02017   0.01268  -0.0078   1.0000   0.8016
  -2.500  -0.3565   0.02005   0.01255   0.0038   1.0000   0.8704
  -2.250  -0.2340   0.02085   0.01212  -0.0088   1.0000   0.9662
  -2.000  -0.1483   0.02039   0.01080  -0.0219   1.0000   0.9926
  -1.750  -0.1297   0.01977   0.00999  -0.0228   1.0000   1.0000
  -1.500  -0.1350   0.01904   0.00923  -0.0193   1.0000   1.0000
  -1.250  -0.1407   0.01829   0.00843  -0.0158   1.0000   1.0000
  -1.000  -0.1327   0.01776   0.00775  -0.0146   1.0000   1.0000
  -0.750  -0.1104   0.01755   0.00732  -0.0156   1.0000   1.0000
  -0.500  -0.0840   0.01751   0.00706  -0.0169   1.0000   1.0000
  -0.250  -0.0569   0.01757   0.00683  -0.0181   1.0000   1.0000
   0.000  -0.0303   0.01768   0.00676  -0.0190   1.0000   1.0000
   0.250  -0.0044   0.01783   0.00676  -0.0196   1.0000   1.0000
   0.500   0.0209   0.01802   0.00683  -0.0200   1.0000   1.0000
   0.750   0.0457   0.01824   0.00697  -0.0203   1.0000   1.0000
   1.000   0.0699   0.01848   0.00715  -0.0205   1.0000   1.0000
   1.250   0.0938   0.01875   0.00740  -0.0206   1.0000   1.0000
   1.500   0.1172   0.01904   0.00770  -0.0205   1.0000   1.0000
   1.750   0.1403   0.01937   0.00803  -0.0205   1.0000   1.0000
   2.000   0.1630   0.01972   0.00843  -0.0204   1.0000   1.0000
   2.250   0.1854   0.02011   0.00888  -0.0203   1.0000   1.0000
   2.500   0.2073   0.02053   0.00939  -0.0201   1.0000   1.0000
   2.750   0.2288   0.02099   0.00998  -0.0199   1.0000   1.0000
   3.000   0.2499   0.02149   0.01063  -0.0197   1.0000   1.0000
   3.250   0.2706   0.02205   0.01157  -0.0195   1.0000   1.0000
   3.500   0.2907   0.02267   0.01244  -0.0193   1.0000   1.0000
   3.750   0.3101   0.02336   0.01337  -0.0192   1.0000   1.0000
   4.000   0.3288   0.02412   0.01440  -0.0190   1.0000   1.0000
   4.250   0.3465   0.02498   0.01554  -0.0189   1.0000   1.0000
   4.500   0.3632   0.02597   0.01685  -0.0188   1.0000   1.0000
   4.750   0.6695   0.02902   0.01786  -0.0463   0.0993   1.0000
   5.000   0.7122   0.03296   0.02189  -0.0473   0.0901   1.0000
   5.250   0.7445   0.03670   0.02605  -0.0466   0.0891   1.0000
   5.500   0.7703   0.04015   0.03003  -0.0451   0.0888   1.0000
   5.750   0.7896   0.04315   0.03373  -0.0427   0.0868   1.0000
   6.000   0.8068   0.04663   0.03776  -0.0405   0.0861   1.0000
   6.250   0.8245   0.05113   0.04252  -0.0389   0.0887   1.0000
   6.500   0.8384   0.05556   0.04768  -0.0363   0.1011   1.0000
   6.750   0.8486   0.06075   0.05368  -0.0340   0.1255   1.0000
   7.000   0.8026   0.05882   0.05298  -0.0289   0.1665   1.0000
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