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EPPLER 858 AIRFOIL (e858-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 858 AIRFOIL (e858-il)
Reynolds number: 100,000
Max Cl/Cd: 21.5 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e858-il-100000.txt
Download as CSV file: xf-e858-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 858 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.5096   0.08728   0.08197  -0.0763   1.0000   0.0651
 -13.250  -0.5461   0.08042   0.07502  -0.0788   1.0000   0.0644
 -13.000  -0.5851   0.07427   0.06874  -0.0806   1.0000   0.0637
 -12.750  -0.6239   0.06923   0.06357  -0.0813   1.0000   0.0632
 -12.500  -0.6606   0.06534   0.05956  -0.0806   1.0000   0.0629
 -12.250  -0.7681   0.05983   0.05350  -0.0779   1.0000   0.0596
 -12.000  -0.7959   0.05876   0.05244  -0.0741   1.0000   0.0598
 -11.750  -0.7620   0.05809   0.05201  -0.0751   0.9971   0.0621
 -11.500  -0.7569   0.05460   0.04819  -0.0807   0.9846   0.0638
 -11.250  -0.7529   0.05102   0.04409  -0.0844   0.9711   0.0652
 -11.000  -0.7180   0.04878   0.04189  -0.0874   0.9613   0.0680
 -10.750  -0.6946   0.04609   0.03894  -0.0900   0.9494   0.0710
 -10.500  -0.6618   0.04384   0.03665  -0.0926   0.9390   0.0746
 -10.250  -0.6268   0.04149   0.03415  -0.0960   0.9307   0.0805
 -10.000  -0.6011   0.03959   0.03213  -0.0974   0.9177   0.0864
  -9.750  -0.5706   0.03786   0.03049  -0.0988   0.9057   0.0933
  -9.500  -0.5312   0.03562   0.02815  -0.1023   0.8994   0.1041
  -9.250  -0.5073   0.03403   0.02661  -0.1027   0.8857   0.1142
  -9.000  -0.4742   0.03225   0.02503  -0.1043   0.8763   0.1275
  -8.750  -0.4403   0.03044   0.02332  -0.1064   0.8669   0.1440
  -8.500  -0.4094   0.02873   0.02165  -0.1080   0.8563   0.1634
  -8.250  -0.3703   0.02694   0.01999  -0.1110   0.8471   0.1893
  -8.000  -0.3366   0.02552   0.01880  -0.1130   0.8351   0.2186
  -7.750  -0.2896   0.02431   0.01780  -0.1172   0.8252   0.2596
  -7.500  -0.2581   0.02411   0.01770  -0.1178   0.8100   0.2943
  -7.250  -0.2126   0.02441   0.01793  -0.1205   0.7969   0.3292
  -7.000  -0.1648   0.02546   0.01899  -0.1224   0.7825   0.3528
  -6.750  -0.1343   0.02630   0.01976  -0.1218   0.7665   0.3708
  -6.500  -0.0980   0.02708   0.02037  -0.1223   0.7527   0.3886
  -6.250  -0.0532   0.02857   0.02185  -0.1229   0.7384   0.4005
  -6.000  -0.0305   0.02915   0.02234  -0.1211   0.7243   0.4124
  -5.750   0.0053   0.02970   0.02265  -0.1218   0.7127   0.4268
  -5.500   0.0284   0.03048   0.02345  -0.1193   0.6988   0.4343
  -5.250   0.0623   0.03130   0.02414  -0.1189   0.6877   0.4443
  -5.000   0.0774   0.03110   0.02382  -0.1170   0.6762   0.4552
  -4.750   0.1143   0.03209   0.02473  -0.1164   0.6661   0.4627
  -4.500   0.1196   0.03119   0.02365  -0.1144   0.6557   0.4757
  -4.250   0.1616   0.03212   0.02447  -0.1145   0.6467   0.4816
  -4.000   0.1709   0.03205   0.02439  -0.1115   0.6363   0.4904
  -3.750   0.1924   0.03148   0.02362  -0.1113   0.6281   0.5004
  -3.500   0.2173   0.03198   0.02410  -0.1096   0.6197   0.5062
  -3.250   0.2317   0.03161   0.02362  -0.1081   0.6114   0.5157
  -3.000   0.2582   0.03118   0.02299  -0.1084   0.6046   0.5238
  -2.750   0.2770   0.03146   0.02329  -0.1062   0.5968   0.5290
  -2.500   0.2941   0.03123   0.02299  -0.1048   0.5891   0.5364
  -2.250   0.3202   0.03052   0.02199  -0.1061   0.5830   0.5450
  -2.000   0.3398   0.03066   0.02216  -0.1042   0.5763   0.5492
  -1.750   0.3558   0.03070   0.02221  -0.1022   0.5694   0.5544
  -1.500   0.3809   0.03040   0.02175  -0.1024   0.5637   0.5612
  -1.250   0.4140   0.03005   0.02110  -0.1045   0.5590   0.5681
  -1.000   0.4219   0.03022   0.02143  -0.1010   0.5526   0.5718
  -0.750   0.4402   0.03027   0.02148  -0.0995   0.5466   0.5765
  -0.500   0.4677   0.03012   0.02117  -0.0999   0.5416   0.5821
  -0.250   0.5024   0.03002   0.02077  -0.1021   0.5371   0.5895
   0.000   0.5078   0.03026   0.02120  -0.0984   0.5316   0.5932
   0.250   0.5234   0.03050   0.02149  -0.0965   0.5265   0.5977
   0.500   0.5474   0.03058   0.02150  -0.0961   0.5221   0.6029
   0.750   0.5797   0.03058   0.02131  -0.0975   0.5184   0.6096
   1.000   0.6001   0.03090   0.02159  -0.0967   0.5143   0.6150
   1.250   0.6032   0.03144   0.02231  -0.0928   0.5092   0.6194
   1.500   0.6190   0.03179   0.02268  -0.0911   0.5046   0.6249
   1.750   0.6442   0.03197   0.02277  -0.0912   0.5008   0.6312
   2.000   0.6756   0.03210   0.02278  -0.0922   0.4977   0.6375
   2.250   0.7008   0.03259   0.02324  -0.0920   0.4947   0.6435
   2.500   0.6857   0.03382   0.02472  -0.0857   0.4903   0.6485
   2.750   0.6824   0.03489   0.02588  -0.0815   0.4859   0.6546
   3.000   0.6976   0.03540   0.02640  -0.0800   0.4822   0.6606
   3.250   0.7255   0.03557   0.02655  -0.0801   0.4791   0.6674
   3.500   0.7640   0.03569   0.02654  -0.0821   0.4764   0.6766
   3.750   0.7701   0.03684   0.02776  -0.0794   0.4735   0.6835
   4.000   0.2423   0.07522   0.06728  -0.0425   0.4606   0.6524
   4.250   0.2687   0.07600   0.06801  -0.0427   0.4581   0.6600
   4.500   0.2791   0.07813   0.07018  -0.0425   0.4572   0.6661
   4.750   0.2981   0.07984   0.07187  -0.0427   0.4561   0.6737
   5.000   0.3225   0.08140   0.07340  -0.0431   0.4552   0.6819
   5.250   0.3459   0.08314   0.07519  -0.0431   0.4545   0.6906
   5.500   0.2433   0.09733   0.08962  -0.0449   0.4966   0.6853
   5.750   0.2068   0.09893   0.09128  -0.0429   0.4894   0.6876
   6.000   0.2179   0.10029   0.09264  -0.0427   0.4828   0.6964
   6.250   0.2422   0.10193   0.09430  -0.0431   0.4792   0.7073
   6.500   0.2760   0.10411   0.09648  -0.0441   0.4769   0.7208
   6.750   0.3162   0.10704   0.09945  -0.0457   0.4755   0.7359
   7.000   0.2679   0.10780   0.10028  -0.0437   0.4648   0.7382
   7.250   0.2879   0.10953   0.10206  -0.0443   0.4606   0.7537
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