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EPPLER 855 AIRFOIL (e855-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 855 AIRFOIL (e855-il)
Reynolds number: 100,000
Max Cl/Cd: 52.93 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e855-il-100000-n5.txt
Download as CSV file: xf-e855-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4009   0.09611   0.09125  -0.0563   1.0000   0.0220
 -11.000  -0.4487   0.08120   0.07634  -0.0636   1.0000   0.0209
 -10.750  -0.5148   0.06766   0.06261  -0.0716   1.0000   0.0199
 -10.500  -0.5567   0.06103   0.05577  -0.0739   1.0000   0.0194
 -10.250  -0.5865   0.05735   0.05198  -0.0734   1.0000   0.0193
 -10.000  -0.6149   0.05505   0.04959  -0.0710   1.0000   0.0190
  -9.750  -0.6248   0.05114   0.04543  -0.0739   0.9938   0.0192
  -9.500  -0.6102   0.04712   0.04113  -0.0786   0.9848   0.0196
  -9.250  -0.5937   0.04366   0.03739  -0.0817   0.9750   0.0200
  -9.000  -0.5754   0.04065   0.03408  -0.0838   0.9651   0.0207
  -8.750  -0.5549   0.03787   0.03095  -0.0855   0.9557   0.0213
  -8.500  -0.5296   0.03519   0.02793  -0.0872   0.9479   0.0225
  -8.250  -0.5072   0.03299   0.02535  -0.0877   0.9378   0.0241
  -8.000  -0.4816   0.03133   0.02365  -0.0889   0.9290   0.0261
  -7.750  -0.4520   0.02978   0.02192  -0.0904   0.9215   0.0289
  -7.500  -0.4267   0.02813   0.02006  -0.0906   0.9120   0.0315
  -7.250  -0.3950   0.02675   0.01865  -0.0925   0.9058   0.0361
  -7.000  -0.3700   0.02544   0.01725  -0.0927   0.8955   0.0409
  -6.750  -0.3368   0.02428   0.01595  -0.0943   0.8888   0.0488
  -6.500  -0.3088   0.02314   0.01482  -0.0952   0.8788   0.0578
  -6.250  -0.2776   0.02207   0.01369  -0.0966   0.8700   0.0701
  -6.000  -0.2432   0.02102   0.01261  -0.0986   0.8620   0.0873
  -5.750  -0.2123   0.02004   0.01166  -0.1000   0.8518   0.1099
  -5.500  -0.1764   0.01895   0.01065  -0.1024   0.8439   0.1468
  -5.250  -0.1467   0.01790   0.00980  -0.1038   0.8330   0.2048
  -5.000  -0.1166   0.01699   0.00931  -0.1051   0.8224   0.3033
  -4.750  -0.0812   0.01675   0.00918  -0.1066   0.8133   0.3808
  -4.500  -0.0497   0.01676   0.00907  -0.1072   0.8021   0.4207
  -4.250  -0.0181   0.01681   0.00895  -0.1078   0.7913   0.4485
  -4.000   0.0152   0.01686   0.00883  -0.1086   0.7815   0.4694
  -3.750   0.0457   0.01692   0.00872  -0.1090   0.7709   0.4865
  -3.500   0.0750   0.01699   0.00866  -0.1091   0.7604   0.5026
  -3.250   0.1062   0.01708   0.00860  -0.1095   0.7514   0.5187
  -3.000   0.1342   0.01715   0.00857  -0.1094   0.7412   0.5322
  -2.750   0.1629   0.01716   0.00843  -0.1095   0.7318   0.5432
  -2.500   0.1929   0.01715   0.00827  -0.1099   0.7234   0.5519
  -2.250   0.2200   0.01713   0.00814  -0.1098   0.7141   0.5591
  -2.000   0.2502   0.01711   0.00797  -0.1102   0.7066   0.5660
  -1.750   0.2767   0.01710   0.00786  -0.1101   0.6975   0.5731
  -1.500   0.3058   0.01710   0.00775  -0.1103   0.6905   0.5792
  -1.250   0.3326   0.01711   0.00767  -0.1102   0.6822   0.5865
  -1.000   0.3616   0.01712   0.00759  -0.1104   0.6758   0.5922
  -0.750   0.3873   0.01716   0.00758  -0.1101   0.6677   0.5991
  -0.500   0.4163   0.01719   0.00751  -0.1104   0.6617   0.6057
  -0.250   0.4419   0.01725   0.00756  -0.1101   0.6545   0.6123
   0.000   0.4700   0.01730   0.00754  -0.1102   0.6483   0.6197
   0.250   0.4966   0.01737   0.00759  -0.1100   0.6422   0.6262
   0.500   0.5233   0.01746   0.00764  -0.1100   0.6357   0.6343
   0.750   0.5515   0.01753   0.00767  -0.1100   0.6307   0.6412
   1.000   0.5766   0.01765   0.00780  -0.1097   0.6244   0.6498
   1.250   0.6029   0.01774   0.00792  -0.1095   0.6188   0.6572
   1.500   0.6310   0.01785   0.00798  -0.1096   0.6140   0.6663
   1.750   0.6547   0.01799   0.00819  -0.1089   0.6080   0.6751
   2.000   0.6814   0.01811   0.00833  -0.1088   0.6030   0.6846
   2.250   0.7094   0.01825   0.00846  -0.1089   0.5987   0.6955
   2.500   0.7324   0.01842   0.00873  -0.1081   0.5928   0.7061
   2.750   0.7586   0.01856   0.00891  -0.1079   0.5880   0.7180
   3.000   0.7868   0.01869   0.00906  -0.1080   0.5842   0.7312
   3.250   0.8083   0.01891   0.00942  -0.1070   0.5787   0.7457
   3.500   0.8326   0.01906   0.00966  -0.1064   0.5738   0.7622
   3.750   0.8591   0.01918   0.00984  -0.1061   0.5699   0.7811
   4.000   0.8800   0.01938   0.01020  -0.1048   0.5651   0.8042
   4.250   0.9007   0.01953   0.01051  -0.1034   0.5603   0.8333
   4.500   0.9248   0.01959   0.01072  -0.1026   0.5562   0.8762
   4.750   0.9586   0.01971   0.01096  -0.1040   0.5518   1.0000
   5.000   0.9817   0.02011   0.01143  -0.1036   0.5465   1.0000
   5.250   1.0086   0.02043   0.01177  -0.1038   0.5421   1.0000
   5.500   1.0386   0.02070   0.01201  -0.1044   0.5384   1.0000
   5.750   1.0573   0.02119   0.01264  -0.1032   0.5326   1.0000
   6.000   1.0818   0.02154   0.01306  -0.1029   0.5277   1.0000
   6.250   1.1114   0.02178   0.01331  -0.1033   0.5236   1.0000
   6.500   1.1282   0.02228   0.01396  -0.1017   0.5172   1.0000
   6.750   1.1525   0.02257   0.01431  -0.1012   0.5114   1.0000
   7.000   1.1759   0.02287   0.01469  -0.1006   0.5053   1.0000
   7.250   1.1943   0.02324   0.01518  -0.0992   0.4980   1.0000
   7.500   1.2188   0.02340   0.01539  -0.0986   0.4909   1.0000
   7.750   1.2346   0.02370   0.01580  -0.0966   0.4817   1.0000
   8.000   1.2521   0.02394   0.01615  -0.0949   0.4726   1.0000
   8.250   1.2729   0.02405   0.01631  -0.0936   0.4635   1.0000
   8.500   1.2832   0.02449   0.01691  -0.0908   0.4537   1.0000
   8.750   1.2992   0.02474   0.01724  -0.0888   0.4443   1.0000
   9.000   1.3106   0.02503   0.01764  -0.0861   0.4342   1.0000
   9.250   1.3168   0.02554   0.01830  -0.0827   0.4234   1.0000
   9.500   1.3250   0.02600   0.01887  -0.0797   0.4119   1.0000
   9.750   1.3324   0.02651   0.01947  -0.0766   0.3993   1.0000
  10.000   1.3375   0.02716   0.02021  -0.0734   0.3855   1.0000
  10.250   1.3398   0.02800   0.02114  -0.0701   0.3702   1.0000
  10.500   1.3400   0.02906   0.02227  -0.0668   0.3526   1.0000
  10.750   1.3390   0.03030   0.02354  -0.0636   0.3329   1.0000
  11.000   1.3355   0.03185   0.02509  -0.0606   0.3104   1.0000
  11.250   1.3293   0.03376   0.02692  -0.0577   0.2862   1.0000
  11.500   1.3207   0.03611   0.02918  -0.0551   0.2616   1.0000
  11.750   1.3100   0.03887   0.03184  -0.0528   0.2393   1.0000
  12.000   1.2988   0.04195   0.03485  -0.0510   0.2184   1.0000
  12.250   1.2877   0.04525   0.03807  -0.0496   0.2003   1.0000
  12.500   1.2777   0.04866   0.04144  -0.0485   0.1840   1.0000
  12.750   1.2689   0.05212   0.04488  -0.0478   0.1685   1.0000
  13.000   1.2611   0.05563   0.04837  -0.0472   0.1548   1.0000
  13.500   1.2490   0.06261   0.05535  -0.0467   0.1310   1.0000
  13.750   1.2451   0.06602   0.05879  -0.0467   0.1204   1.0000
  14.000   1.2414   0.06949   0.06228  -0.0468   0.1111   1.0000
  14.250   1.2372   0.07309   0.06587  -0.0470   0.1028   1.0000
  14.500   1.2365   0.07636   0.06922  -0.0472   0.0945   1.0000
  14.750   1.2333   0.07998   0.07287  -0.0476   0.0876   1.0000
  15.000   1.2328   0.08336   0.07634  -0.0481   0.0805   1.0000
  15.250   1.2307   0.08696   0.07995  -0.0486   0.0746   1.0000
  15.500   1.2301   0.09047   0.08356  -0.0493   0.0686   1.0000
  15.750   1.2278   0.09420   0.08728  -0.0500   0.0640   1.0000
  16.000   1.2285   0.09764   0.09087  -0.0508   0.0586   1.0000
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