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EPPLER 855 AIRFOIL (e855-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 855 AIRFOIL (e855-il)
Reynolds number: 100,000
Max Cl/Cd: 47.02 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e855-il-100000.txt
Download as CSV file: xf-e855-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 855 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3751   0.10575   0.10141  -0.0486   1.0000   0.1299
  -9.500  -0.3835   0.08391   0.08018  -0.0503   1.0000   0.0736
  -9.250  -0.3717   0.08715   0.08349  -0.0435   1.0000   0.0753
  -9.000  -0.3917   0.08159   0.07799  -0.0438   0.9996   0.0676
  -8.750  -0.5135   0.06171   0.05783  -0.0617   0.9905   0.0611
  -8.500  -0.5028   0.05513   0.05113  -0.0661   0.9840   0.0578
  -8.250  -0.5964   0.06411   0.05971  -0.0600   0.9936   0.0585
  -8.000  -0.5812   0.05680   0.05206  -0.0665   0.9843   0.0553
  -7.750  -0.5730   0.04712   0.04101  -0.0731   0.9727   0.0497
  -7.500  -0.5462   0.04289   0.03618  -0.0759   0.9633   0.0494
  -7.250  -0.5170   0.03889   0.03187  -0.0785   0.9553   0.0510
  -7.000  -0.4788   0.03659   0.02935  -0.0818   0.9485   0.0551
  -6.750  -0.4469   0.03425   0.02643  -0.0832   0.9388   0.0594
  -6.500  -0.4059   0.03143   0.02352  -0.0865   0.9341   0.0662
  -6.250  -0.3759   0.02956   0.02146  -0.0871   0.9240   0.0750
  -6.000  -0.3372   0.02779   0.01966  -0.0895   0.9176   0.0894
  -5.750  -0.3040   0.02629   0.01825  -0.0909   0.9088   0.1078
  -5.500  -0.2695   0.02475   0.01685  -0.0925   0.9011   0.1344
  -5.250  -0.2345   0.02309   0.01548  -0.0945   0.8935   0.1794
  -5.000  -0.2038   0.02101   0.01439  -0.0965   0.8857   0.3131
  -4.750  -0.1657   0.02126   0.01488  -0.0976   0.8782   0.4422
  -4.500  -0.1311   0.02178   0.01530  -0.0978   0.8698   0.4834
  -4.250  -0.0909   0.02213   0.01556  -0.0989   0.8634   0.5144
  -4.000  -0.0504   0.02233   0.01560  -0.1003   0.8572   0.5408
  -3.750  -0.0162   0.02251   0.01573  -0.1005   0.8489   0.5591
  -3.500   0.0305   0.02243   0.01555  -0.1028   0.8450   0.5784
  -3.250   0.0545   0.02258   0.01562  -0.1015   0.8337   0.5934
  -3.000   0.0923   0.02253   0.01549  -0.1025   0.8273   0.6103
  -2.750   0.1211   0.02252   0.01537  -0.1022   0.8180   0.6243
  -2.500   0.1529   0.02237   0.01510  -0.1028   0.8097   0.6371
  -2.250   0.1873   0.02215   0.01473  -0.1040   0.8019   0.6487
  -2.000   0.2128   0.02211   0.01463  -0.1034   0.7928   0.6566
  -1.750   0.2493   0.02181   0.01416  -0.1052   0.7858   0.6666
  -1.500   0.2717   0.02185   0.01416  -0.1042   0.7765   0.6738
  -1.250   0.3081   0.02159   0.01373  -0.1060   0.7699   0.6829
  -1.000   0.3284   0.02171   0.01383  -0.1048   0.7608   0.6902
  -0.750   0.3632   0.02152   0.01351  -0.1063   0.7546   0.6988
  -0.500   0.3831   0.02168   0.01366  -0.1051   0.7459   0.7065
  -0.250   0.4158   0.02156   0.01344  -0.1061   0.7397   0.7148
   0.000   0.4368   0.02176   0.01363  -0.1052   0.7320   0.7231
   0.250   0.4649   0.02177   0.01359  -0.1054   0.7256   0.7315
   0.500   0.4917   0.02189   0.01366  -0.1055   0.7193   0.7409
   0.750   0.5127   0.02207   0.01387  -0.1044   0.7120   0.7493
   1.000   0.5475   0.02200   0.01371  -0.1058   0.7074   0.7597
   1.250   0.5597   0.02248   0.01429  -0.1035   0.6995   0.7692
   1.500   0.5881   0.02252   0.01432  -0.1036   0.6943   0.7799
   1.750   0.6098   0.02281   0.01464  -0.1028   0.6882   0.7917
   2.000   0.6296   0.02314   0.01501  -0.1018   0.6817   0.8047
   2.250   0.6594   0.02315   0.01502  -0.1020   0.6776   0.8185
   2.500   0.6695   0.02377   0.01577  -0.0994   0.6705   0.8339
   2.750   0.6920   0.02394   0.01599  -0.0985   0.6651   0.8516
   3.000   0.7214   0.02386   0.01594  -0.0984   0.6615   0.8726
   3.250   0.7206   0.02478   0.01707  -0.0941   0.6538   0.9020
   3.500   0.7601   0.02480   0.01719  -0.0964   0.6491   0.9447
   3.750   0.8211   0.02471   0.01705  -0.1033   0.6456   1.0000
   4.000   0.8256   0.02630   0.01873  -0.1020   0.6370   1.0000
   4.250   0.8641   0.02650   0.01886  -0.1044   0.6329   1.0000
   4.500   0.8833   0.02747   0.01983  -0.1040   0.6271   1.0000
   4.750   0.8958   0.02865   0.02106  -0.1026   0.6203   1.0000
   5.000   0.9352   0.02866   0.02104  -0.1045   0.6168   1.0000
   5.250   0.9297   0.03067   0.02314  -0.1006   0.6085   1.0000
   5.500   0.9564   0.03117   0.02367  -0.1008   0.6035   1.0000
   5.750   1.0037   0.03074   0.02325  -0.1034   0.6005   1.0000
   6.000   0.9761   0.03379   0.02642  -0.0968   0.5899   1.0000
   6.250   1.0238   0.03317   0.02583  -0.0993   0.5865   1.0000
   6.500   0.9956   0.03638   0.02913  -0.0929   0.5760   1.0000
   6.750   1.0455   0.03549   0.02831  -0.0953   0.5721   1.0000
   7.000   1.1121   0.03386   0.02671  -0.0999   0.5694   1.0000
   7.250   1.0692   0.03759   0.03056  -0.0915   0.5574   1.0000
   7.500   1.0578   0.03979   0.03282  -0.0870   0.5485   1.0000
   7.750   1.1087   0.03847   0.03163  -0.0891   0.5427   1.0000
   8.000   1.2255   0.03359   0.02677  -0.0989   0.5385   1.0000
   8.250   1.2019   0.03591   0.02925  -0.0922   0.5275   1.0000
   8.500   1.2381   0.03512   0.02856  -0.0925   0.5189   1.0000
   8.750   1.2958   0.03313   0.02662  -0.0955   0.5099   1.0000
   9.000   1.2994   0.03385   0.02748  -0.0918   0.4994   1.0000
   9.250   1.3413   0.03256   0.02629  -0.0928   0.4891   1.0000
   9.500   1.3883   0.03096   0.02469  -0.0944   0.4772   1.0000
   9.750   1.3983   0.03091   0.02479  -0.0912   0.4646   1.0000
  10.000   1.4083   0.03077   0.02478  -0.0879   0.4515   1.0000
  10.250   1.4173   0.03052   0.02462  -0.0843   0.4378   1.0000
  10.500   1.4229   0.03033   0.02453  -0.0802   0.4232   1.0000
  10.750   1.4255   0.03032   0.02460  -0.0760   0.4072   1.0000
  11.000   1.4269   0.03041   0.02472  -0.0717   0.3891   1.0000
  11.250   1.4175   0.03131   0.02570  -0.0668   0.3697   1.0000
  11.500   1.4077   0.03249   0.02691  -0.0623   0.3467   1.0000
  11.750   1.3950   0.03423   0.02861  -0.0583   0.3207   1.0000
  12.000   1.3805   0.03649   0.03073  -0.0547   0.2918   1.0000
  12.250   1.3650   0.03927   0.03330  -0.0517   0.2636   1.0000
  12.500   1.3497   0.04242   0.03621  -0.0492   0.2380   1.0000
  12.750   1.3355   0.04578   0.03936  -0.0473   0.2153   1.0000
  13.000   1.3243   0.04913   0.04253  -0.0457   0.1951   1.0000
  13.250   1.3153   0.05244   0.04573  -0.0445   0.1768   1.0000
  13.500   1.3093   0.05559   0.04874  -0.0434   0.1606   1.0000
  13.750   1.3061   0.05856   0.05161  -0.0426   0.1461   1.0000
  14.000   1.3042   0.06151   0.05451  -0.0418   0.1327   1.0000
  14.250   1.3041   0.06437   0.05732  -0.0412   0.1206   1.0000
  14.500   1.3058   0.06712   0.06003  -0.0406   0.1098   1.0000
  14.750   1.3102   0.06962   0.06244  -0.0399   0.0998   1.0000
  15.000   1.3102   0.07265   0.06551  -0.0398   0.0916   1.0000
  15.250   1.3133   0.07555   0.06851  -0.0394   0.0839   1.0000
  15.500   1.3223   0.07772   0.07053  -0.0388   0.0759   1.0000
  15.750   1.3175   0.08160   0.07469  -0.0392   0.0709   1.0000
  16.000   1.3278   0.08378   0.07673  -0.0386   0.0641   1.0000
  16.250   1.3213   0.08799   0.08126  -0.0392   0.0606   1.0000
  16.500   1.3211   0.09129   0.08461  -0.0397   0.0564   1.0000
  16.750   1.3247   0.09463   0.08805  -0.0397   0.0523   1.0000
  17.000   1.3159   0.09938   0.09310  -0.0409   0.0498   1.0000
  17.250   1.3100   0.10372   0.09763  -0.0421   0.0474   1.0000
  17.500   1.3204   0.10616   0.09992  -0.0420   0.0435   1.0000
  17.750   1.3036   0.11211   0.10621  -0.0443   0.0427   1.0000
  18.000   1.2875   0.11833   0.11274  -0.0470   0.0421   1.0000
  18.250   1.2704   0.12498   0.11967  -0.0501   0.0416   1.0000
  18.500   1.2505   0.13235   0.12732  -0.0540   0.0413   1.0000
  18.750   1.2286   0.14043   0.13565  -0.0586   0.0414   1.0000
  19.000   1.2043   0.14941   0.14486  -0.0641   0.0418   1.0000
  19.250   1.1787   0.15926   0.15490  -0.0704   0.0425   1.0000
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