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EPPLER 856 AIRFOIL (e856-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 856 AIRFOIL (e856-il)
Reynolds number: 100,000
Max Cl/Cd: 28.59 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e856-il-100000.txt
Download as CSV file: xf-e856-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2626   0.13196   0.12817  -0.0349   1.0000   0.1303
 -11.000  -0.4619   0.08426   0.07971  -0.0706   1.0000   0.0580
 -10.750  -0.4768   0.08051   0.07599  -0.0701   1.0000   0.0575
 -10.500  -0.5030   0.07674   0.07227  -0.0696   1.0000   0.0572
 -10.250  -0.5244   0.07410   0.06970  -0.0678   1.0000   0.0566
 -10.000  -0.5579   0.07193   0.06760  -0.0655   1.0000   0.0562
  -9.750  -0.5891   0.07043   0.06617  -0.0625   1.0000   0.0554
  -9.500  -0.6087   0.06301   0.05837  -0.0725   0.9861   0.0537
  -9.250  -0.6080   0.05667   0.05154  -0.0793   0.9733   0.0537
  -9.000  -0.5970   0.05129   0.04561  -0.0838   0.9613   0.0545
  -8.750  -0.5802   0.04666   0.04043  -0.0867   0.9498   0.0550
  -8.500  -0.5597   0.04273   0.03593  -0.0886   0.9387   0.0560
  -8.250  -0.5345   0.03956   0.03208  -0.0902   0.9283   0.0578
  -8.000  -0.4954   0.03703   0.02962  -0.0935   0.9222   0.0627
  -7.750  -0.4678   0.03487   0.02702  -0.0943   0.9111   0.0678
  -7.500  -0.4248   0.03268   0.02482  -0.0976   0.9061   0.0762
  -7.250  -0.3976   0.03100   0.02318  -0.0980   0.8949   0.0848
  -7.000  -0.3536   0.02900   0.02113  -0.1012   0.8904   0.1002
  -6.750  -0.3270   0.02764   0.01977  -0.1014   0.8790   0.1157
  -6.500  -0.2841   0.02566   0.01801  -0.1045   0.8747   0.1413
  -6.250  -0.2578   0.02429   0.01680  -0.1048   0.8637   0.1694
  -6.000  -0.2158   0.02219   0.01514  -0.1083   0.8587   0.2315
  -5.750  -0.1889   0.02123   0.01482  -0.1087   0.8477   0.3313
  -5.500  -0.1391   0.02161   0.01516  -0.1118   0.8418   0.4096
  -5.250  -0.1072   0.02222   0.01565  -0.1116   0.8303   0.4423
  -5.000  -0.0573   0.02282   0.01619  -0.1140   0.8240   0.4689
  -4.750  -0.0295   0.02331   0.01661  -0.1130   0.8118   0.4873
  -4.500   0.0112   0.02362   0.01679  -0.1143   0.8036   0.5059
  -4.250   0.0407   0.02391   0.01699  -0.1138   0.7925   0.5204
  -4.000   0.0685   0.02408   0.01703  -0.1132   0.7817   0.5344
  -3.750   0.1045   0.02411   0.01688  -0.1142   0.7731   0.5495
  -3.500   0.1256   0.02440   0.01711  -0.1124   0.7619   0.5610
  -3.250   0.1622   0.02446   0.01704  -0.1132   0.7548   0.5731
  -3.000   0.1792   0.02446   0.01693  -0.1115   0.7435   0.5845
  -2.750   0.2111   0.02448   0.01683  -0.1117   0.7361   0.5943
  -2.500   0.2309   0.02441   0.01667  -0.1105   0.7261   0.6032
  -2.250   0.2634   0.02431   0.01641  -0.1112   0.7195   0.6116
  -2.000   0.2814   0.02426   0.01629  -0.1100   0.7101   0.6196
  -1.750   0.3141   0.02415   0.01605  -0.1107   0.7041   0.6266
  -1.500   0.3323   0.02414   0.01595  -0.1099   0.6952   0.6350
  -1.250   0.3611   0.02407   0.01580  -0.1098   0.6888   0.6408
  -1.000   0.3841   0.02413   0.01579  -0.1094   0.6819   0.6481
  -0.750   0.4073   0.02416   0.01575  -0.1090   0.6750   0.6550
  -0.500   0.4395   0.02410   0.01558  -0.1097   0.6700   0.6620
  -0.250   0.4570   0.02432   0.01576  -0.1087   0.6626   0.6696
   0.000   0.4817   0.02437   0.01580  -0.1081   0.6566   0.6757
   0.250   0.5162   0.02433   0.01562  -0.1095   0.6523   0.6841
   0.500   0.5276   0.02476   0.01613  -0.1072   0.6454   0.6903
   0.750   0.5519   0.02491   0.01627  -0.1068   0.6399   0.6979
   1.000   0.5857   0.02490   0.01614  -0.1080   0.6358   0.7065
   1.250   0.5968   0.02543   0.01677  -0.1055   0.6294   0.7138
   1.500   0.6196   0.02570   0.01702  -0.1052   0.6240   0.7226
   1.750   0.6484   0.02579   0.01710  -0.1053   0.6201   0.7312
   2.000   0.6696   0.02622   0.01754  -0.1047   0.6156   0.7409
   2.250   0.6784   0.02690   0.01835  -0.1019   0.6094   0.7500
   2.500   0.7051   0.02706   0.01850  -0.1019   0.6050   0.7604
   2.750   0.7387   0.02712   0.01851  -0.1030   0.6017   0.7733
   3.000   0.7360   0.02828   0.01987  -0.0986   0.5959   0.7843
   3.250   0.7467   0.02901   0.02070  -0.0962   0.5908   0.7975
   3.500   0.7759   0.02910   0.02080  -0.0965   0.5873   0.8135
   3.750   0.8103   0.02902   0.02071  -0.0973   0.5844   0.8325
   4.000   0.7765   0.03139   0.02339  -0.0889   0.5765   0.8536
   4.250   0.7857   0.03209   0.02425  -0.0862   0.5723   0.8852
   4.500   0.8387   0.03179   0.02404  -0.0905   0.5696   0.9479
   4.750   0.9024   0.03156   0.02368  -0.0975   0.5671   1.0000
   5.000   0.8096   0.03755   0.02987  -0.0840   0.5550   1.0000
   5.250   0.8575   0.03739   0.02962  -0.0873   0.5529   1.0000
   5.500   0.9153   0.03680   0.02895  -0.0917   0.5513   1.0000
   5.750   0.7216   0.05188   0.04418  -0.0735   0.5321   1.0000
   6.000   0.7921   0.04870   0.04095  -0.0757   0.5328   1.0000
   6.250   0.8663   0.04580   0.03800  -0.0791   0.5332   1.0000
   6.500   0.6251   0.06890   0.06125  -0.0687   0.5109   1.0000
   6.750   0.6218   0.07218   0.06453  -0.0684   0.5065   1.0000
   7.000   0.6533   0.07264   0.06498  -0.0686   0.5027   1.0000
   7.250   0.7149   0.07064   0.06294  -0.0694   0.5001   1.0000
   7.500   0.6399   0.07996   0.07234  -0.0680   0.4939   1.0000
   7.750   0.6402   0.08304   0.07544  -0.0679   0.4901   1.0000
   8.000   0.7101   0.08016   0.07254  -0.0682   0.4841   1.0000
   8.250   0.6273   0.09268   0.08519  -0.0696   0.5025   1.0000
   8.500   0.6438   0.09532   0.08786  -0.0702   0.5013   1.0000
   8.750   0.7414   0.08654   0.07898  -0.0676   0.4673   1.0000
   9.000   0.6714   0.10166   0.09427  -0.0715   0.4994   1.0000
   9.250   0.6259   0.10586   0.09853  -0.0705   0.4946   1.0000
   9.500   0.6723   0.10414   0.09679  -0.0695   0.4702   1.0000
   9.750   0.6761   0.10763   0.10033  -0.0701   0.4696   1.0000
  10.000   0.7959   0.09643   0.08907  -0.0665   0.4342   1.0000
  10.250   0.7522   0.10333   0.09603  -0.0669   0.4236   1.0000
  10.500   0.8081   0.10101   0.09375  -0.0662   0.4185   1.0000
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