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EPPLER E850 AIRFOIL (e850-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E850 AIRFOIL (e850-il)
Reynolds number: 1,000,000
Max Cl/Cd: 105.79 at α=1.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e850-il-1000000.txt
Download as CSV file: xf-e850-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4385   0.09119   0.08970  -0.0267   1.0000   0.0056
  -9.250  -0.4441   0.08738   0.08591  -0.0267   1.0000   0.0056
  -9.000  -0.4507   0.08358   0.08212  -0.0266   1.0000   0.0057
  -8.750  -0.4499   0.07815   0.07671  -0.0295   0.9994   0.0059
  -8.500  -0.4495   0.07233   0.07089  -0.0331   0.9984   0.0059
  -8.250  -0.4500   0.06602   0.06458  -0.0374   0.9972   0.0059
  -8.000  -0.4531   0.05849   0.05706  -0.0436   0.9956   0.0058
  -7.750  -0.4728   0.04663   0.04511  -0.0588   0.9913   0.0051
  -7.500  -0.4714   0.04019   0.03850  -0.0649   0.9870   0.0052
  -7.250  -0.4619   0.03469   0.03283  -0.0693   0.9845   0.0054
  -7.000  -0.4465   0.02972   0.02766  -0.0729   0.9828   0.0057
  -6.750  -0.4272   0.02518   0.02291  -0.0759   0.9817   0.0062
  -6.500  -0.4139   0.02176   0.01928  -0.0762   0.9779   0.0068
  -6.250  -0.3951   0.01844   0.01571  -0.0767   0.9748   0.0077
  -6.000  -0.3701   0.01583   0.01287  -0.0775   0.9731   0.0091
  -5.750  -0.3367   0.01625   0.01313  -0.0777   0.9722   0.0108
  -5.500  -0.3105   0.01354   0.01011  -0.0788   0.9710   0.0109
  -5.250  -0.3134   0.01934   0.01512  -0.0798   0.9704   0.0124
  -5.000  -0.2838   0.01741   0.01305  -0.0810   0.9697   0.0144
  -4.750  -0.2525   0.01602   0.01149  -0.0820   0.9692   0.0173
  -4.500  -0.2191   0.01542   0.01077  -0.0829   0.9688   0.0212
  -4.250  -1.2480   0.06364   0.06202   0.2358   0.9815   0.0050
  -4.000  -0.1756   0.01028   0.00521  -0.0786   0.9622   0.0070
  -3.750  -0.1452   0.00933   0.00409  -0.0790   0.9609   0.0048
  -3.500  -0.1134   0.00891   0.00360  -0.0798   0.9600   0.0041
  -3.250  -0.0812   0.00833   0.00283  -0.0808   0.9592   0.0038
  -3.000  -0.0482   0.00809   0.00242  -0.0819   0.9586   0.0037
  -2.750  -0.0149   0.00791   0.00220  -0.0831   0.9580   0.0040
  -2.500   0.0178   0.00765   0.00202  -0.0844   0.9574   0.0335
  -2.250   0.0492   0.00691   0.00179  -0.0858   0.9567   0.1845
  -2.000   0.0787   0.00572   0.00165  -0.0873   0.9559   0.4918
  -1.750   0.1011   0.00556   0.00171  -0.0862   0.9519   0.5611
  -1.500   0.1307   0.00547   0.00165  -0.0866   0.9496   0.5755
  -1.250   0.1626   0.00536   0.00156  -0.0876   0.9476   0.5883
  -1.000   0.1962   0.00523   0.00145  -0.0888   0.9456   0.5989
  -0.750   0.2300   0.00509   0.00134  -0.0902   0.9434   0.6075
  -0.500   0.2563   0.00502   0.00130  -0.0898   0.9382   0.6159
  -0.250   0.2870   0.00491   0.00121  -0.0904   0.9335   0.6251
   0.000   0.3178   0.00481   0.00114  -0.0910   0.9285   0.6343
   0.250   0.3449   0.00473   0.00110  -0.0908   0.9208   0.6440
   0.500   0.3732   0.00467   0.00106  -0.0908   0.9125   0.6544
   1.000   0.4269   0.00456   0.00100  -0.0901   0.8830   0.6774
   1.250   0.4529   0.00454   0.00098  -0.0895   0.8599   0.6898
   1.500   0.4803   0.00454   0.00111  -0.0894   0.8520   0.7034
   2.000   0.5178   0.00518   0.00123  -0.0851   0.6782   0.7331
   2.250   0.5299   0.00604   0.00152  -0.0819   0.5217   0.7505
   2.500   0.5434   0.00709   0.00187  -0.0794   0.3315   0.7701
   2.750   0.5603   0.00801   0.00223  -0.0775   0.1718   0.7920
   3.000   0.5806   0.00865   0.00256  -0.0763   0.0758   0.8173
   3.250   0.5995   0.00956   0.00334  -0.0742   0.0063   0.8476
   3.500   0.6197   0.01007   0.00415  -0.0723   0.0055   0.8886
   3.750   0.6438   0.01009   0.00433  -0.0714   0.0046   0.9752
   4.000   0.6694   0.01070   0.00503  -0.0709   0.0040   1.0000
   4.250   0.6936   0.01122   0.00560  -0.0702   0.0034   1.0000
   4.500   0.7181   0.01168   0.00607  -0.0696   0.0026   1.0000
   4.750   0.7362   0.01392   0.00854  -0.0673   0.0020   1.0000
   5.750   0.8012   0.03377   0.03031  -0.0544   0.0057   1.0000
   6.000   0.8311   0.03331   0.02990  -0.0540   0.0047   1.0000
   6.250   0.8486   0.03612   0.03292  -0.0517   0.0042   1.0000
   6.500   0.8615   0.03981   0.03686  -0.0490   0.0039   1.0000
   6.750   0.8717   0.04381   0.04111  -0.0462   0.0037   1.0000
   7.000   0.8797   0.04794   0.04546  -0.0436   0.0035   1.0000
   7.250   0.8850   0.05227   0.05000  -0.0410   0.0034   1.0000
   7.500   0.8876   0.05670   0.05461  -0.0385   0.0033   1.0000
   7.750   0.8874   0.06113   0.05920  -0.0363   0.0032   1.0000
   8.000   0.8833   0.06570   0.06392  -0.0343   0.0032   1.0000
   8.250   0.8768   0.06994   0.06828  -0.0326   0.0031   1.0000
   8.500   0.8629   0.07390   0.07232  -0.0303   0.0031   1.0000
   8.750   0.8448   0.07776   0.07626  -0.0284   0.0032   1.0000
   9.000   0.8268   0.08238   0.08093  -0.0289   0.0032   1.0000
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