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EPPLER 864 STRUT AIRFOIL (e864-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 864 STRUT AIRFOIL (e864-il)
Reynolds number: 200,000
Max Cl/Cd: 15 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e864-il-200000-n5.txt
Download as CSV file: xf-e864-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 864 STRUT AIRFOIL                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.2932   0.10835   0.10017  -0.0338   0.5174   0.2788
 -12.750  -0.2700   0.10797   0.09977  -0.0346   0.5138   0.2796
 -12.500  -0.3008   0.10111   0.09283  -0.0352   0.5128   0.2907
 -12.250  -0.2762   0.10092   0.09260  -0.0360   0.5094   0.2912
 -12.000  -0.2518   0.10070   0.09233  -0.0367   0.5063   0.2918
 -11.750  -0.2281   0.10041   0.09199  -0.0375   0.5035   0.2926
 -11.500  -0.2617   0.09348   0.08496  -0.0378   0.5028   0.3040
 -11.250  -0.2364   0.09332   0.08482  -0.0386   0.5005   0.3044
 -11.000  -0.2114   0.09313   0.08463  -0.0393   0.4981   0.3050
 -10.750  -0.1870   0.09286   0.08437  -0.0401   0.4957   0.3057
 -10.500  -0.1636   0.09248   0.08399  -0.0408   0.4933   0.3066
 -10.250  -0.1419   0.09190   0.08339  -0.0415   0.4911   0.3078
 -10.000  -0.1233   0.09097   0.08244  -0.0422   0.4890   0.3095
  -9.250  -0.1631   0.07806   0.06935  -0.0425   0.4855   0.3317
  -9.000  -0.1373   0.07799   0.06924  -0.0432   0.4833   0.3323
  -8.750  -0.1123   0.07785   0.06905  -0.0439   0.4811   0.3329
  -8.500  -0.0882   0.07758   0.06878  -0.0445   0.4792   0.3337
  -8.250  -0.0656   0.07711   0.06833  -0.0452   0.4774   0.3347
  -8.000  -0.0450   0.07644   0.06767  -0.0457   0.4757   0.3361
  -7.750  -0.0306   0.07519   0.06642  -0.0462   0.4742   0.3388
  -7.500  -0.4909   0.03529   0.02577  -0.0283   0.4811   0.3913
  -7.250  -0.4596   0.03535   0.02586  -0.0293   0.4791   0.3922
  -7.000  -0.4302   0.03534   0.02590  -0.0301   0.4771   0.3932
  -6.750  -0.4031   0.03526   0.02586  -0.0307   0.4753   0.3943
  -6.500  -0.3802   0.03500   0.02562  -0.0310   0.4735   0.3957
  -6.250  -0.3660   0.03432   0.02494  -0.0306   0.4718   0.3974
  -6.000  -0.3670   0.03300   0.02356  -0.0288   0.4704   0.3998
  -5.750  -0.3800   0.03133   0.02178  -0.0254   0.4692   0.4024
  -5.500  -0.3961   0.02982   0.02013  -0.0211   0.4680   0.4050
  -5.250  -0.4158   0.02860   0.01875  -0.0154   0.4669   0.4073
  -5.000  -0.4094   0.02821   0.01830  -0.0128   0.4655   0.4089
  -4.750  -0.3837   0.02811   0.01822  -0.0130   0.4639   0.4100
  -4.500  -0.3621   0.02802   0.01812  -0.0126   0.4623   0.4112
  -4.250  -0.3435   0.02794   0.01800  -0.0116   0.4607   0.4123
  -4.000  -0.3258   0.02787   0.01788  -0.0105   0.4591   0.4135
  -3.750  -0.3081   0.02773   0.01776  -0.0095   0.4577   0.4149
  -3.500  -0.2907   0.02759   0.01764  -0.0084   0.4564   0.4163
  -3.250  -0.2739   0.02746   0.01751  -0.0072   0.4550   0.4179
  -3.000  -0.2575   0.02731   0.01734  -0.0059   0.4536   0.4196
  -2.750  -0.2413   0.02714   0.01714  -0.0046   0.4522   0.4213
  -2.500  -0.2248   0.02695   0.01691  -0.0034   0.4507   0.4229
  -2.250  -0.2077   0.02677   0.01667  -0.0022   0.4492   0.4243
  -2.000  -0.1903   0.02660   0.01642  -0.0010   0.4477   0.4256
  -1.750  -0.1672   0.02646   0.01627  -0.0008   0.4462   0.4269
  -1.500  -0.1407   0.02639   0.01623  -0.0011   0.4446   0.4282
  -1.250  -0.1153   0.02636   0.01620  -0.0012   0.4432   0.4295
  -1.000  -0.0903   0.02635   0.01619  -0.0012   0.4420   0.4308
  -0.750  -0.0651   0.02635   0.01617  -0.0013   0.4408   0.4320
  -0.500  -0.0399   0.02638   0.01617  -0.0014   0.4396   0.4333
  -0.250  -0.0166   0.02642   0.01622  -0.0012   0.4384   0.4347
   0.000   0.0045   0.02644   0.01629  -0.0006   0.4370   0.4361
   0.250   0.0253   0.02648   0.01636   0.0000   0.4354   0.4376
   0.500   0.0460   0.02651   0.01641   0.0007   0.4338   0.4393
   0.750   0.0668   0.02655   0.01645   0.0013   0.4322   0.4409
   1.000   0.0878   0.02658   0.01647   0.0019   0.4308   0.4424
   1.250   0.1091   0.02662   0.01649   0.0024   0.4294   0.4437
   1.500   0.1305   0.02665   0.01649   0.0030   0.4280   0.4449
   1.750   0.1538   0.02665   0.01649   0.0032   0.4266   0.4462
   2.000   0.1782   0.02664   0.01651   0.0032   0.4252   0.4475
   2.250   0.2028   0.02665   0.01655   0.0032   0.4239   0.4489
   2.500   0.2276   0.02670   0.01660   0.0032   0.4227   0.4504
   2.750   0.2531   0.02678   0.01668   0.0031   0.4215   0.4519
   3.000   0.2800   0.02692   0.01679   0.0027   0.4204   0.4535
   3.250   0.2956   0.02716   0.01710   0.0041   0.4191   0.4549
   3.500   0.3068   0.02744   0.01747   0.0061   0.4176   0.4563
   3.750   0.3165   0.02773   0.01783   0.0084   0.4159   0.4577
   4.000   0.3249   0.02802   0.01817   0.0109   0.4141   0.4591
   4.250   0.3286   0.02827   0.01847   0.0142   0.4123   0.4605
   4.500   0.3349   0.02855   0.01877   0.0169   0.4106   0.4619
   4.750   0.3461   0.02884   0.01907   0.0187   0.4090   0.4633
   5.000   0.3628   0.02910   0.01931   0.0197   0.4075   0.4648
   5.250   0.3839   0.02925   0.01944   0.0200   0.4061   0.4664
   5.500   0.4092   0.02926   0.01947   0.0198   0.4047   0.4682
   5.750   0.4385   0.02923   0.01942   0.0190   0.4033   0.4700
   6.000   0.4395   0.03007   0.02036   0.0216   0.4012   0.4714
   6.250   0.3933   0.03286   0.02340   0.0285   0.3974   0.4722
   6.500   0.3529   0.03628   0.02698   0.0332   0.3931   0.4730
   6.750   0.3580   0.03757   0.02832   0.0340   0.3906   0.4745
   7.000   0.3821   0.03777   0.02851   0.0335   0.3892   0.4763
   7.250   0.4122   0.03761   0.02833   0.0327   0.3881   0.4783
   7.500   0.4444   0.03737   0.02805   0.0318   0.3871   0.4804
   7.750   0.4788   0.03704   0.02767   0.0307   0.3862   0.4826
   8.000   0.0991   0.07091   0.06214   0.0446   0.3429   0.4767
   8.250   0.0649   0.07709   0.06839   0.0452   0.3324   0.4774
   8.500   0.0854   0.07774   0.06904   0.0446   0.3307   0.4792
   8.750   0.1084   0.07814   0.06943   0.0439   0.3295   0.4811
   9.000   0.1322   0.07847   0.06975   0.0433   0.3287   0.4831
   9.250   0.1046   0.08428   0.07562   0.0435   0.3191   0.4838
   9.500   0.1238   0.08511   0.07644   0.0428   0.3172   0.4856
  10.250   0.1528   0.09068   0.08213   0.0412   0.3066   0.4911
  10.500   0.1681   0.09197   0.08346   0.0406   0.3041   0.4932
  10.750   0.1887   0.09265   0.08419   0.0399   0.3027   0.4956
  11.000   0.2112   0.09313   0.08469   0.0391   0.3017   0.4981
  11.250   0.2352   0.09343   0.08501   0.0384   0.3009   0.5007
  11.500   0.2606   0.09356   0.08515   0.0376   0.3003   0.5034
  11.750   0.2869   0.09358   0.08516   0.0368   0.2997   0.5062
  12.000   0.2594   0.09981   0.09145   0.0364   0.2885   0.5072
  12.250   0.2833   0.10011   0.09175   0.0356   0.2877   0.5097
  12.500   0.2922   0.10217   0.09386   0.0349   0.2842   0.5120
  12.750   0.3281   0.10102   0.09275   0.0340   0.2856   0.5155
  13.000   0.3066   0.10674   0.09856   0.0334   0.2756   0.5170
  13.250   0.3296   0.10713   0.09899   0.0326   0.2746   0.5205
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