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EPPLER 856 AIRFOIL (e856-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 856 AIRFOIL (e856-il)
Reynolds number: 50,000
Max Cl/Cd: 18.81 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e856-il-50000-n5.txt
Download as CSV file: xf-e856-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 856 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4019   0.09518   0.08837  -0.0662   1.0000   0.0497
 -11.250  -0.4257   0.08854   0.08176  -0.0686   1.0000   0.0495
 -11.000  -0.4521   0.08246   0.07569  -0.0707   1.0000   0.0491
 -10.750  -0.4784   0.07735   0.07058  -0.0718   1.0000   0.0487
 -10.500  -0.5088   0.07280   0.06603  -0.0723   1.0000   0.0484
 -10.250  -0.5389   0.06931   0.06253  -0.0715   1.0000   0.0481
 -10.000  -0.5699   0.06672   0.05994  -0.0694   1.0000   0.0477
  -9.750  -0.6008   0.06454   0.05777  -0.0672   0.9988   0.0475
  -9.500  -0.6020   0.05916   0.05191  -0.0733   0.9853   0.0485
  -9.250  -0.5917   0.05487   0.04718  -0.0774   0.9730   0.0504
  -9.000  -0.5700   0.05240   0.04461  -0.0799   0.9617   0.0533
  -8.750  -0.5516   0.04922   0.04103  -0.0819   0.9496   0.0563
  -8.500  -0.5302   0.04675   0.03836  -0.0833   0.9377   0.0600
  -8.250  -0.5071   0.04468   0.03608  -0.0845   0.9261   0.0649
  -8.000  -0.4812   0.04271   0.03397  -0.0856   0.9155   0.0704
  -7.750  -0.4512   0.04076   0.03176  -0.0872   0.9065   0.0787
  -7.500  -0.4286   0.03929   0.03028  -0.0875   0.8944   0.0868
  -7.250  -0.4032   0.03774   0.02868  -0.0883   0.8841   0.0973
  -7.000  -0.3748   0.03609   0.02697  -0.0895   0.8751   0.1109
  -6.750  -0.3535   0.03466   0.02553  -0.0896   0.8634   0.1257
  -6.500  -0.3214   0.03286   0.02372  -0.0916   0.8567   0.1488
  -6.250  -0.3029   0.03148   0.02247  -0.0915   0.8442   0.1726
  -6.000  -0.2784   0.02998   0.02115  -0.0924   0.8343   0.2113
  -5.750  -0.2497   0.02883   0.02046  -0.0935   0.8256   0.2724
  -5.500  -0.2242   0.02878   0.02063  -0.0930   0.8147   0.3331
  -5.250  -0.1864   0.02897   0.02065  -0.0942   0.8073   0.3861
  -5.000  -0.1617   0.02935   0.02087  -0.0932   0.7957   0.4169
  -4.750  -0.1232   0.02956   0.02082  -0.0942   0.7891   0.4462
  -4.500  -0.1016   0.02992   0.02102  -0.0927   0.7773   0.4656
  -4.250  -0.0683   0.03010   0.02099  -0.0928   0.7697   0.4861
  -4.000  -0.0439   0.03030   0.02104  -0.0917   0.7594   0.5029
  -3.750  -0.0145   0.03037   0.02092  -0.0915   0.7511   0.5192
  -3.500   0.0114   0.03037   0.02075  -0.0909   0.7419   0.5337
  -3.250   0.0399   0.03023   0.02038  -0.0912   0.7338   0.5479
  -3.000   0.0649   0.03027   0.02031  -0.0902   0.7249   0.5572
  -2.750   0.0947   0.03004   0.01986  -0.0908   0.7176   0.5679
  -2.500   0.1176   0.03001   0.01969  -0.0901   0.7086   0.5763
  -2.250   0.1529   0.02968   0.01913  -0.0915   0.7029   0.5855
  -2.000   0.1693   0.02981   0.01919  -0.0899   0.6931   0.5925
  -1.750   0.2038   0.02952   0.01867  -0.0914   0.6873   0.6016
  -1.500   0.2213   0.02969   0.01879  -0.0899   0.6786   0.6079
  -1.250   0.2519   0.02954   0.01844  -0.0909   0.6723   0.6170
  -1.000   0.2766   0.02959   0.01841  -0.0904   0.6658   0.6232
  -0.750   0.2976   0.02973   0.01846  -0.0898   0.6582   0.6309
  -0.500   0.3308   0.02960   0.01818  -0.0908   0.6533   0.6386
  -0.250   0.3464   0.02995   0.01851  -0.0892   0.6456   0.6457
   0.000   0.3726   0.03005   0.01850  -0.0894   0.6396   0.6539
   0.250   0.4065   0.02996   0.01830  -0.0904   0.6354   0.6617
   0.500   0.4171   0.03055   0.01888  -0.0884   0.6274   0.6701
   0.750   0.4423   0.03070   0.01899  -0.0881   0.6221   0.6776
   1.000   0.4775   0.03064   0.01880  -0.0895   0.6183   0.6876
   1.250   0.4816   0.03147   0.01973  -0.0863   0.6105   0.6950
   1.500   0.5064   0.03173   0.01994  -0.0863   0.6055   0.7052
   1.750   0.5390   0.03170   0.01986  -0.0870   0.6018   0.7151
   2.000   0.5419   0.03270   0.02094  -0.0839   0.5945   0.7250
   2.250   0.5609   0.03317   0.02142  -0.0830   0.5893   0.7366
   2.500   0.5905   0.03325   0.02150  -0.0832   0.5858   0.7489
   2.750   0.5975   0.03417   0.02250  -0.0807   0.5798   0.7617
   3.000   0.6033   0.03513   0.02356  -0.0781   0.5735   0.7763
   3.250   0.6292   0.03529   0.02375  -0.0778   0.5698   0.7940
   3.500   0.6618   0.03519   0.02370  -0.0783   0.5672   0.8153
   3.750   0.6262   0.03781   0.02656  -0.0708   0.5574   0.8398
   4.000   0.6531   0.03804   0.02692  -0.0709   0.5536   0.8833
   4.250   0.7013   0.03787   0.02675  -0.0746   0.5510   1.0000
   4.750   0.6907   0.04250   0.03134  -0.0701   0.5366   1.0000
   5.000   0.7270   0.04263   0.03138  -0.0716   0.5342   1.0000
   5.500   0.7095   0.04844   0.03717  -0.0674   0.5189   1.0000
   5.750   0.7428   0.04858   0.03727  -0.0681   0.5169   1.0000
   6.250   0.7262   0.05527   0.04400  -0.0654   0.5011   1.0000
   6.750   0.7154   0.06192   0.05068  -0.0639   0.4863   1.0000
   7.000   0.7439   0.06233   0.05108  -0.0640   0.4839   1.0000
   7.250   0.7141   0.06779   0.05659  -0.0628   0.4732   1.0000
   7.500   0.7359   0.06879   0.05761  -0.0628   0.4696   1.0000
   7.750   0.7638   0.06925   0.05809  -0.0628   0.4671   1.0000
   8.750   0.7614   0.08117   0.07019  -0.0614   0.4397   1.0000
   9.000   0.7836   0.08213   0.07119  -0.0612   0.4360   1.0000
   9.500   0.7882   0.08765   0.07683  -0.0609   0.4224   1.0000
   9.750   0.8129   0.08833   0.07758  -0.0608   0.4189   1.0000
  10.000   0.8016   0.09240   0.08171  -0.0607   0.4096   1.0000
  10.250   0.8186   0.09376   0.08315  -0.0606   0.4046   1.0000
  10.500   0.8472   0.09398   0.08345  -0.0603   0.4016   1.0000
  10.750   0.8293   0.09876   0.08830  -0.0606   0.3906   1.0000
  11.000   0.8537   0.09932   0.08895  -0.0603   0.3868   1.0000
  11.250   0.8439   0.10336   0.09306  -0.0606   0.3768   1.0000
  11.500   0.8640   0.10430   0.09410  -0.0604   0.3720   1.0000
  11.750   0.8616   0.10761   0.09749  -0.0607   0.3631   1.0000
  12.000   0.8776   0.10888   0.09887  -0.0605   0.3570   1.0000
  12.500   0.8925   0.11331   0.10349  -0.0608   0.3419   1.0000
  12.750   0.9181   0.11337   0.10367  -0.0602   0.3380   1.0000
  13.000   0.9085   0.11758   0.10796  -0.0610   0.3266   1.0000
  13.500   0.9251   0.12171   0.11230  -0.0614   0.3111   1.0000
  14.000   0.9427   0.12565   0.11644  -0.0618   0.2954   1.0000
  14.250   0.9415   0.12904   0.11994  -0.0627   0.2857   1.0000
  14.500   0.9616   0.12926   0.12029  -0.0622   0.2797   1.0000
  14.750   0.9565   0.13336   0.12447  -0.0636   0.2692   1.0000
  15.000   0.9806   0.13284   0.12408  -0.0628   0.2640   1.0000
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