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EPPLER 434 AIRFOIL (e434-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 434 AIRFOIL (e434-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.9 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e434-il-1000000-n5.txt
Download as CSV file: xf-e434-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 434 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.0809   0.05818   0.05553  -0.0966   0.7355   0.0050
  -7.500  -0.2071   0.03479   0.03147  -0.1118   0.7225   0.0034
  -7.250  -0.2417   0.02202   0.01774  -0.1059   0.7190   0.0032
  -7.000  -0.2293   0.01897   0.01424  -0.1040   0.7156   0.0031
  -6.750  -0.2116   0.01686   0.01176  -0.1027   0.7123   0.0031
  -6.500  -0.1902   0.01543   0.01005  -0.1018   0.7094   0.0031
  -6.250  -0.1670   0.01432   0.00874  -0.1012   0.7066   0.0031
  -6.000  -0.1428   0.01345   0.00771  -0.1007   0.7036   0.0031
  -5.750  -0.1182   0.01269   0.00680  -0.1002   0.7003   0.0031
  -5.500  -0.0933   0.01208   0.00606  -0.0998   0.6973   0.0031
  -5.250  -0.0680   0.01153   0.00540  -0.0994   0.6944   0.0031
  -5.000  -0.0420   0.01107   0.00488  -0.0992   0.6917   0.0032
  -4.750  -0.0160   0.01062   0.00436  -0.0989   0.6886   0.0032
  -4.500   0.0104   0.01028   0.00396  -0.0987   0.6855   0.0033
  -4.250   0.0368   0.00997   0.00359  -0.0986   0.6825   0.0033
  -4.000   0.0634   0.00971   0.00326  -0.0984   0.6795   0.0034
  -3.750   0.0905   0.00943   0.00296  -0.0983   0.6768   0.0035
  -3.500   0.1175   0.00915   0.00265  -0.0983   0.6737   0.0040
  -3.250   0.1448   0.00899   0.00246  -0.0983   0.6704   0.0045
  -3.000   0.1722   0.00884   0.00228  -0.0982   0.6671   0.0051
  -2.750   0.1994   0.00870   0.00211  -0.0982   0.6640   0.0063
  -2.500   0.2272   0.00856   0.00197  -0.0983   0.6611   0.0090
  -2.250   0.2549   0.00841   0.00185  -0.0984   0.6576   0.0149
  -2.000   0.2822   0.00825   0.00175  -0.0984   0.6541   0.0311
  -1.750   0.3089   0.00802   0.00165  -0.0984   0.6506   0.0708
  -1.500   0.3357   0.00774   0.00158  -0.0985   0.6473   0.1366
  -1.250   0.3623   0.00740   0.00151  -0.0986   0.6435   0.2277
  -1.000   0.3892   0.00714   0.00146  -0.0987   0.6395   0.3077
  -0.750   0.4155   0.00684   0.00141  -0.0987   0.6354   0.4081
  -0.500   0.4413   0.00633   0.00136  -0.0988   0.6316   0.5672
  -0.250   0.4666   0.00588   0.00140  -0.0985   0.6270   0.7321
   0.000   0.4938   0.00587   0.00144  -0.0984   0.6221   0.7729
   0.250   0.5215   0.00591   0.00147  -0.0984   0.6175   0.7901
   0.500   0.5494   0.00593   0.00151  -0.0985   0.6123   0.8043
   0.750   0.5765   0.00599   0.00156  -0.0984   0.6066   0.8226
   1.000   0.6035   0.00606   0.00164  -0.0982   0.6013   0.8395
   1.250   0.6303   0.00612   0.00171  -0.0980   0.5952   0.8501
   1.500   0.6577   0.00620   0.00175  -0.0980   0.5891   0.8542
   1.750   0.6860   0.00625   0.00178  -0.0983   0.5827   0.8561
   2.000   0.7132   0.00633   0.00182  -0.0982   0.5754   0.8578
   2.250   0.7407   0.00639   0.00186  -0.0983   0.5683   0.8595
   2.500   0.7674   0.00648   0.00192  -0.0982   0.5598   0.8615
   2.750   0.7946   0.00656   0.00198  -0.0983   0.5511   0.8637
   3.000   0.8212   0.00667   0.00206  -0.0982   0.5420   0.8658
   3.250   0.8477   0.00679   0.00214  -0.0981   0.5310   0.8679
   3.500   0.8742   0.00691   0.00222  -0.0981   0.5199   0.8699
   3.750   0.9003   0.00705   0.00232  -0.0979   0.5084   0.8719
   4.000   0.9253   0.00720   0.00244  -0.0976   0.4952   0.8739
   4.250   0.9500   0.00737   0.00257  -0.0971   0.4811   0.8760
   4.500   0.9741   0.00756   0.00272  -0.0966   0.4650   0.8785
   4.750   0.9975   0.00779   0.00289  -0.0960   0.4467   0.8813
   5.000   1.0203   0.00806   0.00308  -0.0953   0.4274   0.8840
   5.250   1.0426   0.00835   0.00328  -0.0945   0.4077   0.8866
   5.500   1.0642   0.00863   0.00350  -0.0936   0.3879   0.8892
   5.750   1.0849   0.00892   0.00374  -0.0925   0.3685   0.8920
   6.000   1.1043   0.00927   0.00400  -0.0911   0.3477   0.8953
   6.250   1.1236   0.00961   0.00427  -0.0898   0.3270   0.8988
   6.500   1.1415   0.01000   0.00457  -0.0883   0.3059   0.9024
   6.750   1.1569   0.01036   0.00487  -0.0862   0.2859   0.9067
   7.000   1.1713   0.01069   0.00516  -0.0838   0.2692   0.9119
   7.500   1.1976   0.01146   0.00585  -0.0788   0.2360   0.9238
   7.750   1.2096   0.01191   0.00624  -0.0763   0.2193   0.9317
   8.000   1.2207   0.01232   0.00664  -0.0735   0.2049   0.9426
   8.250   1.2319   0.01280   0.00710  -0.0709   0.1889   0.9623
   8.750   1.2617   0.01404   0.00822  -0.0679   0.1559   1.0000
   9.000   1.2742   0.01469   0.00882  -0.0660   0.1426   1.0000
   9.250   1.2856   0.01542   0.00949  -0.0640   0.1290   1.0000
   9.500   1.2964   0.01621   0.01024  -0.0620   0.1158   1.0000
   9.750   1.3072   0.01704   0.01102  -0.0601   0.1039   1.0000
  10.000   1.3170   0.01795   0.01188  -0.0582   0.0919   1.0000
  10.250   1.3276   0.01886   0.01276  -0.0565   0.0822   1.0000
  10.500   1.3397   0.01971   0.01362  -0.0550   0.0748   1.0000
  10.750   1.3501   0.02070   0.01458  -0.0534   0.0672   1.0000
  11.000   1.3589   0.02181   0.01567  -0.0518   0.0588   1.0000
  11.250   1.3700   0.02281   0.01668  -0.0504   0.0530   1.0000
  11.500   1.3795   0.02395   0.01780  -0.0489   0.0469   1.0000
  11.750   1.3872   0.02524   0.01907  -0.0474   0.0400   1.0000
  12.000   1.3953   0.02654   0.02037  -0.0460   0.0343   1.0000
  12.250   1.4043   0.02779   0.02164  -0.0448   0.0301   1.0000
  12.500   1.4120   0.02918   0.02304  -0.0435   0.0257   1.0000
  13.000   1.4250   0.03226   0.02612  -0.0410   0.0180   1.0000
  13.250   1.4333   0.03372   0.02762  -0.0400   0.0156   1.0000
  13.500   1.4399   0.03536   0.02928  -0.0390   0.0132   1.0000
  13.750   1.4460   0.03709   0.03104  -0.0381   0.0112   1.0000
  14.000   1.4535   0.03873   0.03272  -0.0373   0.0097   1.0000
  14.250   1.4589   0.04060   0.03462  -0.0365   0.0081   1.0000
  14.500   1.4653   0.04245   0.03652  -0.0358   0.0070   1.0000
  14.750   1.4709   0.04441   0.03853  -0.0352   0.0059   1.0000
  15.000   1.4768   0.04638   0.04056  -0.0347   0.0053   1.0000
  15.250   1.4811   0.04857   0.04280  -0.0342   0.0045   1.0000
  15.500   1.4864   0.05071   0.04501  -0.0339   0.0039   1.0000
  15.750   1.4902   0.05306   0.04742  -0.0336   0.0034   1.0000
  16.000   1.4939   0.05548   0.04992  -0.0334   0.0030   1.0000
  16.250   1.4973   0.05798   0.05248  -0.0334   0.0027   1.0000
  16.500   1.4993   0.06071   0.05528  -0.0333   0.0023   1.0000
  16.750   1.5010   0.06356   0.05821  -0.0335   0.0020   1.0000
  17.000   1.5021   0.06654   0.06127  -0.0337   0.0017   1.0000
  17.250   1.5029   0.06959   0.06441  -0.0341   0.0015   1.0000
  17.500   1.5024   0.07289   0.06779  -0.0346   0.0014   1.0000
  17.750   1.5018   0.07631   0.07130  -0.0352   0.0012   1.0000
  18.000   1.5001   0.07994   0.07502  -0.0359   0.0010   1.0000
  18.250   1.4986   0.08362   0.07880  -0.0368   0.0010   1.0000
  18.500   1.4954   0.08761   0.08289  -0.0379   0.0008   1.0000
  18.750   1.4916   0.09176   0.08714  -0.0392   0.0008   1.0000
  19.000   1.4863   0.09625   0.09173  -0.0406   0.0007   1.0000
  19.250   1.4813   0.10077   0.09635  -0.0422   0.0006   1.0000
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