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EPPLER EA 8(-1)-006 AIRFOIL (ea81006-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER EA 8(-1)-006 AIRFOIL (ea81006-il)
Reynolds number: 1,000,000
Max Cl/Cd: 66.02 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ea81006-il-1000000-n5.txt
Download as CSV file: xf-ea81006-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER EA 8(-1)-006 AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.8531   0.09011   0.08845   0.0029   1.0000   0.0028
 -12.000  -0.8921   0.07777   0.07614  -0.0056   1.0000   0.0028
 -11.500  -1.0491   0.04351   0.04134  -0.0219   1.0000   0.0025
 -11.250  -1.0689   0.03662   0.03403  -0.0197   1.0000   0.0025
 -11.000  -1.0719   0.03169   0.02873  -0.0178   1.0000   0.0025
 -10.750  -1.0642   0.02844   0.02519  -0.0162   1.0000   0.0026
 -10.500  -1.0512   0.02604   0.02256  -0.0150   1.0000   0.0026
 -10.250  -1.0367   0.02391   0.02018  -0.0137   1.0000   0.0027
 -10.000  -1.0193   0.02230   0.01837  -0.0126   1.0000   0.0027
  -9.750  -1.0008   0.02084   0.01669  -0.0116   1.0000   0.0028
  -9.500  -0.9807   0.01964   0.01533  -0.0107   1.0000   0.0029
  -9.250  -0.9597   0.01861   0.01414  -0.0099   1.0000   0.0029
  -9.000  -0.9402   0.01721   0.01252  -0.0089   1.0000   0.0031
  -8.750  -0.9195   0.01602   0.01115  -0.0079   1.0000   0.0033
  -8.500  -0.8971   0.01523   0.01025  -0.0072   1.0000   0.0036
  -8.250  -0.8740   0.01463   0.00959  -0.0065   1.0000   0.0039
  -8.000  -0.8509   0.01400   0.00889  -0.0058   1.0000   0.0042
  -7.750  -0.8277   0.01340   0.00820  -0.0051   1.0000   0.0045
  -7.500  -0.8043   0.01286   0.00757  -0.0043   1.0000   0.0048
  -7.250  -0.7809   0.01236   0.00700  -0.0036   1.0000   0.0050
  -7.000  -0.7573   0.01192   0.00650  -0.0028   1.0000   0.0052
  -6.750  -0.7343   0.01137   0.00585  -0.0019   1.0000   0.0058
  -6.500  -0.7113   0.01087   0.00529  -0.0010   1.0000   0.0067
  -6.250  -0.6882   0.01043   0.00482  -0.0001   1.0000   0.0078
  -6.000  -0.6649   0.01007   0.00439   0.0008   1.0000   0.0089
  -5.750  -0.6414   0.00976   0.00405   0.0016   1.0000   0.0104
  -5.500  -0.6186   0.00939   0.00368   0.0026   1.0000   0.0153
  -5.250  -0.5956   0.00910   0.00346   0.0035   1.0000   0.0250
  -5.000  -0.5660   0.00897   0.00333   0.0030   0.9988   0.0298
  -4.750  -0.5343   0.00894   0.00333   0.0021   0.9969   0.0328
  -4.500  -0.5024   0.00885   0.00325   0.0011   0.9947   0.0346
  -4.250  -0.4683   0.00880   0.00320  -0.0003   0.9902   0.0360
  -4.000  -0.4326   0.00890   0.00330  -0.0021   0.9856   0.0381
  -3.750  -0.3983   0.00861   0.00300  -0.0036   0.9788   0.0390
  -3.500  -0.3627   0.00837   0.00275  -0.0054   0.9698   0.0398
  -3.250  -0.3288   0.00818   0.00254  -0.0067   0.9539   0.0404
  -3.000  -0.2991   0.00806   0.00237  -0.0070   0.9263   0.0412
  -2.750  -0.2743   0.00800   0.00219  -0.0061   0.8854   0.0420
  -2.500  -0.2507   0.00800   0.00201  -0.0050   0.8335   0.0426
  -2.250  -0.2277   0.00812   0.00183  -0.0039   0.7548   0.0432
  -2.000  -0.2089   0.00894   0.00174  -0.0023   0.4770   0.0438
  -1.750  -0.1867   0.00970   0.00168  -0.0016   0.1995   0.0443
  -1.500  -0.1614   0.00997   0.00162  -0.0012   0.0632   0.0447
  -1.250  -0.1345   0.00990   0.00152  -0.0010   0.0590   0.0454
  -1.000  -0.1079   0.00980   0.00139  -0.0008   0.0563   0.0469
  -0.750  -0.0810   0.00974   0.00132  -0.0006   0.0550   0.0481
  -0.500  -0.0540   0.00970   0.00128  -0.0004   0.0541   0.0492
  -0.250  -0.0270   0.00968   0.00126  -0.0002   0.0529   0.0503
   0.000   0.0000   0.00967   0.00125   0.0000   0.0515   0.0515
   0.250   0.0270   0.00968   0.00126   0.0002   0.0503   0.0529
   0.500   0.0540   0.00970   0.00128   0.0004   0.0492   0.0541
   0.750   0.0810   0.00974   0.00132   0.0006   0.0481   0.0550
   1.000   0.1079   0.00980   0.00139   0.0008   0.0469   0.0563
   1.250   0.1345   0.00991   0.00152   0.0010   0.0454   0.0589
   1.750   0.1867   0.00970   0.00168   0.0016   0.0443   0.1979
   2.000   0.2088   0.00893   0.00174   0.0023   0.0438   0.4779
   2.250   0.2277   0.00812   0.00183   0.0039   0.0432   0.7540
   2.500   0.2507   0.00801   0.00201   0.0050   0.0426   0.8334
   2.750   0.2744   0.00800   0.00219   0.0061   0.0419   0.8842
   3.000   0.2991   0.00806   0.00237   0.0070   0.0412   0.9263
   3.250   0.3286   0.00818   0.00254   0.0068   0.0404   0.9539
   3.500   0.3627   0.00836   0.00275   0.0054   0.0397   0.9701
   3.750   0.3977   0.00861   0.00301   0.0037   0.0391   0.9783
   4.000   0.4321   0.00893   0.00333   0.0022   0.0382   0.9855
   4.250   0.4682   0.00879   0.00318   0.0004   0.0359   0.9901
   4.500   0.5019   0.00886   0.00325  -0.0010   0.0346   0.9945
   4.750   0.5340   0.00893   0.00332  -0.0020   0.0326   0.9968
   5.000   0.5656   0.00897   0.00334  -0.0029   0.0299   0.9987
   5.250   0.5956   0.00910   0.00347  -0.0035   0.0252   1.0000
   5.500   0.6185   0.00938   0.00367  -0.0026   0.0155   1.0000
   5.750   0.6413   0.00976   0.00405  -0.0016   0.0105   1.0000
   6.000   0.6648   0.01007   0.00439  -0.0007   0.0089   1.0000
   6.250   0.6881   0.01043   0.00482   0.0001   0.0077   1.0000
   6.500   0.7112   0.01086   0.00529   0.0010   0.0067   1.0000
   6.750   0.7342   0.01137   0.00585   0.0019   0.0058   1.0000
   7.000   0.7571   0.01192   0.00650   0.0029   0.0052   1.0000
   7.250   0.7807   0.01236   0.00701   0.0036   0.0050   1.0000
   7.500   0.8042   0.01285   0.00756   0.0044   0.0048   1.0000
   7.750   0.8275   0.01340   0.00820   0.0051   0.0045   1.0000
   8.000   0.8507   0.01400   0.00889   0.0058   0.0042   1.0000
   8.250   0.8739   0.01463   0.00959   0.0065   0.0039   1.0000
   8.500   0.8970   0.01524   0.01026   0.0072   0.0036   1.0000
   8.750   0.9194   0.01605   0.01119   0.0079   0.0033   1.0000
   9.000   0.9400   0.01724   0.01256   0.0089   0.0030   1.0000
   9.250   0.9599   0.01856   0.01409   0.0099   0.0029   1.0000
   9.500   0.9808   0.01962   0.01530   0.0107   0.0029   1.0000
   9.750   1.0008   0.02083   0.01669   0.0116   0.0028   1.0000
  10.000   1.0192   0.02231   0.01838   0.0126   0.0027   1.0000
  10.250   1.0365   0.02398   0.02026   0.0137   0.0027   1.0000
  10.500   1.0527   0.02576   0.02225   0.0148   0.0026   1.0000
  10.750   1.0639   0.02850   0.02526   0.0162   0.0026   1.0000
  11.000   1.0703   0.03202   0.02909   0.0179   0.0025   1.0000
  11.250   1.0696   0.03652   0.03392   0.0197   0.0025   1.0000
  11.500   1.0450   0.04417   0.04204   0.0220   0.0025   1.0000
  12.000   0.9120   0.07345   0.07183   0.0091   0.0027   1.0000
  12.250   0.8491   0.09119   0.08953  -0.0038   0.0029   1.0000
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