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EPPLER E852 AIRFOIL (e852-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E852 AIRFOIL (e852-il)
Reynolds number: 200,000
Max Cl/Cd: 84.21 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e852-il-200000.txt
Download as CSV file: xf-e852-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E852 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4308   0.08958   0.08625  -0.0446   1.0000   0.0411
  -8.500  -0.4459   0.08552   0.08229  -0.0475   1.0000   0.0421
  -8.250  -0.4649   0.08184   0.07877  -0.0485   1.0000   0.0422
  -8.000  -0.4820   0.07949   0.07651  -0.0462   1.0000   0.0420
  -7.750  -0.4999   0.07772   0.07482  -0.0427   1.0000   0.0417
  -7.000  -0.5021   0.06277   0.05915  -0.0616   0.9869   0.0430
  -6.750  -0.4899   0.05537   0.05192  -0.0639   0.9843   0.0459
  -6.500  -0.4658   0.05113   0.04753  -0.0682   0.9803   0.0487
  -5.500  -0.3570   0.02934   0.02350  -0.0784   0.9609   0.0273
  -5.250  -0.3233   0.02506   0.01855  -0.0796   0.9586   0.0234
  -5.000  -0.2873   0.02218   0.01517  -0.0808   0.9569   0.0218
  -4.750  -0.2603   0.02044   0.01321  -0.0806   0.9523   0.0219
  -4.500  -0.2298   0.01887   0.01153  -0.0812   0.9486   0.0237
  -4.250  -0.1956   0.01754   0.01010  -0.0825   0.9461   0.0285
  -4.000  -0.1592   0.01606   0.00866  -0.0848   0.9441   0.0593
  -3.750  -0.1319   0.01434   0.00757  -0.0858   0.9396   0.1870
  -3.500  -0.1034   0.01322   0.00746  -0.0870   0.9358   0.4749
  -3.250  -0.0690   0.01323   0.00745  -0.0883   0.9329   0.5361
  -3.000  -0.0323   0.01323   0.00740  -0.0900   0.9309   0.5702
  -2.750  -0.0086   0.01335   0.00746  -0.0892   0.9249   0.5947
  -2.500   0.0237   0.01335   0.00741  -0.0901   0.9215   0.6152
  -2.250   0.0589   0.01333   0.00736  -0.0915   0.9192   0.6368
  -2.000   0.0962   0.01329   0.00726  -0.0932   0.9176   0.6605
  -1.750   0.1172   0.01339   0.00736  -0.0920   0.9111   0.6745
  -1.500   0.1510   0.01332   0.00725  -0.0933   0.9082   0.6870
  -1.250   0.1883   0.01319   0.00709  -0.0953   0.9063   0.6986
  -1.000   0.2260   0.01304   0.00692  -0.0974   0.9046   0.7096
  -0.750   0.2479   0.01315   0.00705  -0.0964   0.8985   0.7203
  -0.500   0.2799   0.01309   0.00700  -0.0974   0.8951   0.7321
  -0.250   0.3153   0.01296   0.00690  -0.0989   0.8928   0.7446
   0.000   0.3517   0.01282   0.00680  -0.1007   0.8910   0.7579
   0.250   0.3704   0.01299   0.00704  -0.0991   0.8838   0.7719
   0.500   0.4027   0.01289   0.00700  -0.0999   0.8806   0.7873
   0.750   0.4377   0.01273   0.00691  -0.1013   0.8782   0.8045
   1.000   0.4571   0.01285   0.00714  -0.0997   0.8713   0.8235
   1.250   0.4865   0.01272   0.00714  -0.0998   0.8673   0.8456
   1.500   0.5184   0.01250   0.00703  -0.1002   0.8645   0.8714
   1.750   0.5342   0.01256   0.00723  -0.0975   0.8565   0.9104
   2.000   0.5799   0.01224   0.00703  -0.1009   0.8530   0.9661
   2.250   0.6166   0.01219   0.00706  -0.1031   0.8463   1.0000
   2.500   0.6525   0.01200   0.00689  -0.1045   0.8395   1.0000
   2.750   0.6817   0.01191   0.00683  -0.1046   0.8295   1.0000
   3.000   0.7135   0.01162   0.00656  -0.1047   0.8173   1.0000
   3.250   0.7442   0.01128   0.00624  -0.1045   0.8022   1.0000
   3.500   0.7728   0.01109   0.00614  -0.1040   0.7878   1.0000
   3.750   0.8006   0.01095   0.00605  -0.1035   0.7729   1.0000
   4.000   0.8256   0.01082   0.00598  -0.1023   0.7537   1.0000
   4.250   0.8506   0.01067   0.00587  -0.1011   0.7304   1.0000
   4.500   0.8718   0.01060   0.00585  -0.0991   0.6980   1.0000
   4.750   0.8918   0.01059   0.00581  -0.0969   0.6477   1.0000
   5.000   0.9053   0.01101   0.00578  -0.0933   0.5343   1.0000
   5.250   0.9002   0.01274   0.00642  -0.0872   0.3480   1.0000
   5.500   0.8971   0.01484   0.00748  -0.0822   0.1748   1.0000
   5.750   0.9032   0.01660   0.00863  -0.0788   0.0878   1.0000
   6.000   0.9136   0.01819   0.00984  -0.0760   0.0354   1.0000
   6.250   0.9230   0.01999   0.01167  -0.0728   0.0175   1.0000
   6.500   0.9382   0.02137   0.01318  -0.0704   0.0143   1.0000
   6.750   0.9553   0.02291   0.01482  -0.0685   0.0130   1.0000
   7.000   0.9760   0.02473   0.01675  -0.0672   0.0121   1.0000
   7.250   1.0017   0.02706   0.01925  -0.0666   0.0117   1.0000
   7.500   1.0302   0.02993   0.02242  -0.0664   0.0118   1.0000
   7.750   1.0567   0.03366   0.02660  -0.0655   0.0124   1.0000
   8.000   1.0747   0.03841   0.03197  -0.0632   0.0137   1.0000
   8.250   1.0842   0.04307   0.03714  -0.0602   0.0151   1.0000
   8.500   1.0869   0.04765   0.04213  -0.0569   0.0163   1.0000
   8.750   1.0817   0.05294   0.04777  -0.0535   0.0176   1.0000
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