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EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E853 AIRFOIL (e853-il)
Reynolds number: 1,000,000
Max Cl/Cd: 114.37 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e853-il-1000000-n5.txt
Download as CSV file: xf-e853-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E853 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4329   0.08877   0.08716  -0.0501   0.9976   0.0023
 -10.250  -0.4477   0.07835   0.07676  -0.0575   0.9960   0.0022
 -10.000  -0.5286   0.04702   0.04527  -0.0817   0.9911   0.0021
  -9.500  -0.5587   0.03064   0.02813  -0.0990   0.9683   0.0020
  -9.250  -0.5542   0.02628   0.02336  -0.1001   0.9548   0.0020
  -9.000  -0.5345   0.02200   0.01858  -0.1028   0.9454   0.0019
  -8.750  -0.5016   0.01909   0.01527  -0.1065   0.9385   0.0019
  -8.500  -0.4614   0.01694   0.01279  -0.1110   0.9312   0.0019
  -8.000  -0.3947   0.01409   0.00937  -0.1155   0.8977   0.0020
  -7.750  -0.3696   0.01329   0.00835  -0.1156   0.8780   0.0020
  -7.500  -0.3463   0.01253   0.00739  -0.1152   0.8600   0.0020
  -7.250  -0.3225   0.01195   0.00664  -0.1148   0.8439   0.0020
  -7.000  -0.2983   0.01142   0.00596  -0.1144   0.8300   0.0021
  -6.750  -0.2737   0.01094   0.00534  -0.1141   0.8177   0.0021
  -6.500  -0.2485   0.01054   0.00481  -0.1138   0.8062   0.0022
  -6.250  -0.2228   0.01018   0.00435  -0.1136   0.7950   0.0023
  -6.000  -0.1965   0.00989   0.00394  -0.1135   0.7852   0.0024
  -5.750  -0.1703   0.00954   0.00348  -0.1134   0.7764   0.0028
  -5.500  -0.1437   0.00927   0.00315  -0.1133   0.7676   0.0037
  -5.250  -0.1167   0.00907   0.00288  -0.1133   0.7593   0.0047
  -5.000  -0.0898   0.00886   0.00263  -0.1133   0.7515   0.0078
  -4.750  -0.0625   0.00863   0.00241  -0.1134   0.7443   0.0145
  -4.500  -0.0353   0.00845   0.00222  -0.1135   0.7375   0.0232
  -4.250  -0.0080   0.00819   0.00201  -0.1136   0.7306   0.0431
  -4.000   0.0191   0.00792   0.00183  -0.1138   0.7242   0.0740
  -3.750   0.0469   0.00771   0.00168  -0.1139   0.7182   0.0996
  -3.500   0.0743   0.00748   0.00153  -0.1141   0.7124   0.1378
  -3.250   0.1021   0.00723   0.00139  -0.1144   0.7070   0.1815
  -3.000   0.1297   0.00694   0.00124  -0.1146   0.7011   0.2381
  -2.750   0.1572   0.00660   0.00111  -0.1149   0.6962   0.3189
  -2.500   0.1851   0.00633   0.00105  -0.1152   0.6913   0.3901
  -2.250   0.2131   0.00627   0.00102  -0.1154   0.6861   0.4155
  -2.000   0.2412   0.00625   0.00099  -0.1155   0.6815   0.4314
  -1.750   0.2695   0.00621   0.00098  -0.1157   0.6768   0.4495
  -1.500   0.2976   0.00620   0.00098  -0.1158   0.6722   0.4686
  -1.250   0.3258   0.00620   0.00097  -0.1159   0.6680   0.4833
  -1.000   0.3541   0.00619   0.00098  -0.1161   0.6635   0.4937
  -0.750   0.3823   0.00620   0.00098  -0.1162   0.6591   0.5005
  -0.500   0.4104   0.00622   0.00099  -0.1163   0.6552   0.5065
   0.000   0.4669   0.00624   0.00102  -0.1166   0.6467   0.5170
   0.250   0.4949   0.00628   0.00105  -0.1167   0.6427   0.5225
   0.500   0.5232   0.00629   0.00107  -0.1168   0.6387   0.5275
   0.750   0.5513   0.00631   0.00111  -0.1169   0.6342   0.5332
   1.000   0.5790   0.00636   0.00115  -0.1170   0.6289   0.5387
   1.250   0.6070   0.00638   0.00119  -0.1170   0.6218   0.5444
   1.500   0.6343   0.00644   0.00124  -0.1170   0.6138   0.5506
   1.750   0.6620   0.00648   0.00130  -0.1170   0.6047   0.5565
   2.000   0.6893   0.00653   0.00136  -0.1170   0.5944   0.5632
   2.250   0.7163   0.00661   0.00143  -0.1168   0.5822   0.5696
   2.500   0.7428   0.00670   0.00151  -0.1166   0.5647   0.5769
   2.750   0.7686   0.00685   0.00160  -0.1163   0.5424   0.5841
   3.000   0.7947   0.00698   0.00171  -0.1160   0.5221   0.5921
   3.250   0.8200   0.00717   0.00184  -0.1156   0.4948   0.5999
   3.500   0.8436   0.00750   0.00202  -0.1149   0.4530   0.6089
   3.750   0.8639   0.00807   0.00234  -0.1136   0.3841   0.6179
   4.000   0.8847   0.00864   0.00267  -0.1125   0.3251   0.6269
   4.250   0.9036   0.00935   0.00307  -0.1111   0.2517   0.6370
   4.500   0.9227   0.01002   0.00347  -0.1097   0.1878   0.6483
   4.750   0.9449   0.01044   0.00379  -0.1088   0.1526   0.6603
   5.000   0.9672   0.01085   0.00413  -0.1080   0.1239   0.6728
   5.250   0.9887   0.01129   0.00448  -0.1070   0.0947   0.6866
   5.500   1.0100   0.01174   0.00485  -0.1060   0.0685   0.7024
   5.750   1.0309   0.01222   0.00524  -0.1048   0.0448   0.7202
   6.000   1.0524   0.01261   0.00562  -0.1039   0.0303   0.7394
   6.250   1.0739   0.01299   0.00600  -0.1028   0.0202   0.7609
   6.500   1.0956   0.01332   0.00639  -0.1019   0.0149   0.7872
   6.750   1.1165   0.01365   0.00679  -0.1007   0.0105   0.8206
   7.000   1.1357   0.01392   0.00722  -0.0992   0.0073   0.8688
   7.250   1.1501   0.01416   0.00762  -0.0965   0.0041   1.0000
   7.500   1.1699   0.01465   0.00812  -0.0952   0.0026   1.0000
   7.750   1.1899   0.01510   0.00860  -0.0940   0.0021   1.0000
   8.000   1.2084   0.01558   0.00912  -0.0925   0.0018   1.0000
   8.250   1.2246   0.01613   0.00972  -0.0905   0.0016   1.0000
   8.500   1.2396   0.01674   0.01040  -0.0883   0.0014   1.0000
   8.750   1.2529   0.01747   0.01121  -0.0859   0.0013   1.0000
   9.000   1.2677   0.01811   0.01191  -0.0839   0.0013   1.0000
   9.250   1.2817   0.01881   0.01271  -0.0817   0.0013   1.0000
   9.500   1.2953   0.01954   0.01351  -0.0796   0.0013   1.0000
   9.750   1.3080   0.02034   0.01439  -0.0774   0.0013   1.0000
  10.000   1.3198   0.02122   0.01535  -0.0752   0.0012   1.0000
  10.250   1.3301   0.02222   0.01644  -0.0729   0.0012   1.0000
  10.500   1.3410   0.02320   0.01751  -0.0707   0.0012   1.0000
  10.750   1.3510   0.02427   0.01867  -0.0686   0.0012   1.0000
  11.000   1.3613   0.02534   0.01982  -0.0666   0.0011   1.0000
  11.250   1.3693   0.02663   0.02122  -0.0645   0.0011   1.0000
  11.500   1.3779   0.02792   0.02261  -0.0626   0.0011   1.0000
  11.750   1.3862   0.02926   0.02405  -0.0608   0.0011   1.0000
  12.000   1.3943   0.03066   0.02554  -0.0591   0.0010   1.0000
  12.250   1.4002   0.03231   0.02733  -0.0574   0.0010   1.0000
  12.500   1.4049   0.03413   0.02928  -0.0557   0.0010   1.0000
  12.750   1.4107   0.03588   0.03113  -0.0543   0.0010   1.0000
  13.000   1.4153   0.03780   0.03317  -0.0530   0.0009   1.0000
  13.250   1.4172   0.04007   0.03557  -0.0517   0.0009   1.0000
  13.500   1.4185   0.04248   0.03811  -0.0506   0.0009   1.0000
  13.750   1.4166   0.04533   0.04112  -0.0496   0.0009   1.0000
  14.000   1.4153   0.04821   0.04413  -0.0488   0.0009   1.0000
  14.250   1.4119   0.05145   0.04752  -0.0483   0.0009   1.0000
  14.500   1.4077   0.05490   0.05113  -0.0480   0.0009   1.0000
  14.750   1.4013   0.05881   0.05519  -0.0480   0.0009   1.0000
  15.000   1.3938   0.06306   0.05961  -0.0484   0.0009   1.0000
  15.250   1.3847   0.06775   0.06446  -0.0492   0.0009   1.0000
  15.500   1.3744   0.07287   0.06974  -0.0505   0.0009   1.0000
  15.750   1.3644   0.07823   0.07525  -0.0522   0.0008   1.0000
  16.000   1.3479   0.08502   0.08222  -0.0547   0.0009   1.0000
  16.250   1.3328   0.09200   0.08937  -0.0578   0.0008   1.0000
  16.500   1.3157   0.09983   0.09736  -0.0617   0.0009   1.0000
  16.750   1.2978   0.10834   0.10604  -0.0663   0.0009   1.0000
  17.000   1.2757   0.11836   0.11624  -0.0721   0.0009   1.0000
  17.250   1.2531   0.12921   0.12726  -0.0786   0.0009   1.0000
  17.500   1.2279   0.14132   0.13953  -0.0860   0.0009   1.0000
  17.750   1.2013   0.15435   0.15271  -0.0939   0.0009   1.0000
  18.000   1.1724   0.16854   0.16705  -0.1023   0.0009   1.0000
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