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EPPLER 858 AIRFOIL (e858-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 858 AIRFOIL (e858-il)
Reynolds number: 50,000
Max Cl/Cd: 12.99 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e858-il-50000-n5.txt
Download as CSV file: xf-e858-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.3418   0.11254   0.10553  -0.0595   1.0000   0.0735
 -12.750  -0.3707   0.10412   0.09714  -0.0624   1.0000   0.0753
 -12.500  -0.4435   0.08912   0.08192  -0.0691   1.0000   0.0754
 -12.250  -0.4793   0.08218   0.07485  -0.0710   1.0000   0.0761
 -12.000  -0.5079   0.07715   0.06971  -0.0716   1.0000   0.0771
 -11.750  -0.5352   0.07305   0.06549  -0.0713   1.0000   0.0782
 -11.500  -0.5616   0.06976   0.06209  -0.0701   1.0000   0.0792
 -11.250  -0.5382   0.06794   0.06038  -0.0731   0.9932   0.0835
 -11.000  -0.5238   0.06404   0.05631  -0.0782   0.9828   0.0885
 -10.750  -0.5088   0.06069   0.05281  -0.0824   0.9706   0.0944
 -10.500  -0.4889   0.05836   0.05052  -0.0853   0.9572   0.1004
 -10.250  -0.4783   0.05569   0.04779  -0.0874   0.9403   0.1069
 -10.000  -0.4683   0.05290   0.04488  -0.0897   0.9243   0.1144
  -9.750  -0.4536   0.05076   0.04277  -0.0916   0.9094   0.1226
  -9.500  -0.4399   0.04854   0.04056  -0.0933   0.8952   0.1318
  -9.250  -0.4267   0.04624   0.03825  -0.0951   0.8821   0.1422
  -9.000  -0.4211   0.04419   0.03618  -0.0952   0.8660   0.1522
  -8.750  -0.4119   0.04227   0.03425  -0.0954   0.8509   0.1642
  -8.500  -0.3958   0.04039   0.03241  -0.0962   0.8383   0.1795
  -8.250  -0.3771   0.03874   0.03083  -0.0970   0.8257   0.1971
  -8.000  -0.3619   0.03753   0.02971  -0.0966   0.8111   0.2158
  -7.750  -0.3270   0.03650   0.02876  -0.0988   0.8018   0.2425
  -7.500  -0.3072   0.03636   0.02868  -0.0978   0.7864   0.2638
  -7.250  -0.2788   0.03601   0.02822  -0.0984   0.7742   0.2892
  -7.000  -0.2477   0.03609   0.02818  -0.0987   0.7617   0.3115
  -6.750  -0.2237   0.03629   0.02823  -0.0979   0.7483   0.3302
  -6.500  -0.1870   0.03651   0.02823  -0.0988   0.7374   0.3493
  -6.250  -0.1671   0.03688   0.02846  -0.0971   0.7235   0.3635
  -6.000  -0.1228   0.03756   0.02892  -0.0982   0.7135   0.3779
  -5.750  -0.1139   0.03735   0.02857  -0.0958   0.7001   0.3906
  -5.500  -0.0847   0.03687   0.02774  -0.0968   0.6910   0.4071
  -5.250  -0.0635   0.03773   0.02862  -0.0940   0.6780   0.4139
  -5.000  -0.0385   0.03695   0.02750  -0.0949   0.6694   0.4294
  -4.750  -0.0187   0.03766   0.02823  -0.0921   0.6576   0.4355
  -4.500   0.0072   0.03729   0.02759  -0.0923   0.6490   0.4477
  -4.250   0.0247   0.03731   0.02752  -0.0905   0.6390   0.4558
  -4.000   0.0490   0.03738   0.02747  -0.0895   0.6298   0.4641
  -3.750   0.0717   0.03668   0.02649  -0.0899   0.6224   0.4755
  -3.500   0.0872   0.03696   0.02678  -0.0874   0.6126   0.4809
  -3.250   0.1146   0.03670   0.02633  -0.0874   0.6053   0.4894
  -3.000   0.1311   0.03620   0.02562  -0.0868   0.5976   0.4984
  -2.750   0.1491   0.03632   0.02572  -0.0849   0.5893   0.5032
  -2.500   0.1781   0.03608   0.02530  -0.0852   0.5829   0.5099
  -2.250   0.1949   0.03580   0.02486  -0.0845   0.5758   0.5178
  -2.000   0.2104   0.03575   0.02474  -0.0830   0.5683   0.5230
  -1.750   0.2376   0.03564   0.02451  -0.0828   0.5624   0.5280
  -1.500   0.2622   0.03553   0.02425  -0.0826   0.5566   0.5341
  -1.250   0.2716   0.03562   0.02429  -0.0805   0.5491   0.5405
  -1.000   0.2945   0.03554   0.02409  -0.0802   0.5433   0.5459
  -0.750   0.3256   0.03543   0.02385  -0.0807   0.5388   0.5508
  -0.500   0.3364   0.03576   0.02418  -0.0784   0.5328   0.5560
  -0.250   0.3477   0.03605   0.02442  -0.0765   0.5264   0.5620
   0.000   0.3725   0.03603   0.02426  -0.0766   0.5214   0.5681
   0.250   0.4053   0.03595   0.02404  -0.0773   0.5174   0.5731
   0.500   0.4092   0.03659   0.02474  -0.0742   0.5115   0.5779
   0.750   0.4143   0.03723   0.02539  -0.0714   0.5057   0.5835
   1.000   0.4354   0.03749   0.02554  -0.0710   0.5013   0.5903
   1.250   0.4647   0.03754   0.02551  -0.0712   0.4978   0.5957
   1.500   0.4899   0.03777   0.02566  -0.0711   0.4942   0.6017
   1.750   0.4574   0.03955   0.02762  -0.0633   0.4871   0.6058
   2.000   0.4653   0.04039   0.02840  -0.0614   0.4821   0.6123
   2.250   0.4902   0.04061   0.02859  -0.0611   0.4787   0.6182
   2.500   0.5265   0.04054   0.02840  -0.0623   0.4761   0.6261
   2.750   0.4725   0.04436   0.03245  -0.0538   0.4684   0.6292
   3.000   0.4521   0.04726   0.03539  -0.0502   0.4616   0.6346
   3.250   0.4736   0.04772   0.03584  -0.0496   0.4584   0.6411
   3.500   0.5069   0.04755   0.03559  -0.0501   0.4562   0.6499
   3.750   0.5471   0.04711   0.03504  -0.0514   0.4545   0.6600
   4.250   0.4453   0.05894   0.04725  -0.0434   0.4363   0.6660
   4.500   0.4758   0.05884   0.04707  -0.0434   0.4348   0.6773
   6.000   0.4174   0.08141   0.07014  -0.0410   0.4005   0.7272
   6.250   0.4358   0.08257   0.07136  -0.0408   0.3984   0.7448
   6.500   0.4581   0.08327   0.07215  -0.0406   0.3967   0.7672
   6.750   0.4291   0.08890   0.07797  -0.0406   0.3900   0.7801
   7.250   0.4438   0.09295   0.08246  -0.0414   0.3827   1.0000
   7.500   0.4633   0.09479   0.08418  -0.0425   0.3804   1.0000
   7.750   0.4871   0.09614   0.08539  -0.0433   0.3785   1.0000
   8.000   0.4813   0.10001   0.08923  -0.0440   0.3741   1.0000
   8.250   0.4757   0.10372   0.09294  -0.0447   0.3694   1.0000
   8.500   0.4835   0.10639   0.09557  -0.0454   0.3665   1.0000
   8.750   0.4965   0.10860   0.09771  -0.0460   0.3640   1.0000
   9.000   0.5153   0.11025   0.09929  -0.0464   0.3617   1.0000
   9.250   0.5389   0.11150   0.10046  -0.0467   0.3598   1.0000
   9.500   0.5254   0.11580   0.10479  -0.0475   0.3550   1.0000
   9.750   0.5246   0.11904   0.10804  -0.0482   0.3518   1.0000
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