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S8025 (8%) (s8025-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S8025 (8%) (s8025-il)
Reynolds number: 50,000
Max Cl/Cd: 22.69 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8025-il-50000.txt
Download as CSV file: xf-s8025-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8025 (8%)                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.6092   0.09684   0.09040   0.0316   1.0000   0.2896
  -7.750  -0.6675   0.07915   0.07285   0.0037   1.0000   0.1336
  -7.500  -0.6875   0.06801   0.06142  -0.0066   1.0000   0.1101
  -7.250  -0.6831   0.06207   0.05533  -0.0084   1.0000   0.1062
  -7.000  -0.6866   0.05386   0.04628  -0.0121   1.0000   0.0978
  -6.750  -0.6752   0.04868   0.04058  -0.0126   1.0000   0.0979
  -6.500  -0.6580   0.04490   0.03674  -0.0123   1.0000   0.1029
  -6.250  -0.6403   0.04068   0.03203  -0.0120   1.0000   0.1065
  -6.000  -0.6204   0.03643   0.02692  -0.0114   1.0000   0.1114
  -5.750  -0.5984   0.03341   0.02357  -0.0106   1.0000   0.1253
  -5.500  -0.5756   0.03073   0.02093  -0.0097   1.0000   0.1462
  -5.250  -0.5525   0.02833   0.01841  -0.0086   1.0000   0.1771
  -5.000  -0.5295   0.02632   0.01638  -0.0074   1.0000   0.2154
  -4.750  -0.5062   0.02460   0.01472  -0.0061   1.0000   0.2572
  -4.500  -0.4825   0.02302   0.01326  -0.0048   1.0000   0.3025
  -4.250  -0.4589   0.02156   0.01196  -0.0034   1.0000   0.3552
  -4.000  -0.4365   0.02034   0.01104  -0.0017   1.0000   0.4191
  -3.750  -0.4154   0.01929   0.01030   0.0006   1.0000   0.4934
  -3.500  -0.3962   0.01845   0.00985   0.0037   1.0000   0.5731
  -3.250  -0.3787   0.01777   0.00949   0.0077   1.0000   0.6564
  -3.000  -0.3630   0.01726   0.00923   0.0126   1.0000   0.7376
  -2.750  -0.3440   0.01693   0.00905   0.0176   1.0000   0.8182
  -2.500  -0.2857   0.01700   0.00883   0.0158   1.0000   0.9120
  -2.250  -0.1271   0.01649   0.00739  -0.0083   1.0000   1.0000
  -2.000  -0.1161   0.01579   0.00659  -0.0080   1.0000   1.0000
  -1.750  -0.1033   0.01527   0.00599  -0.0072   1.0000   1.0000
  -1.500  -0.0885   0.01490   0.00553  -0.0062   1.0000   1.0000
  -1.250  -0.0721   0.01465   0.00517  -0.0052   1.0000   1.0000
  -1.000  -0.0543   0.01449   0.00492  -0.0042   1.0000   1.0000
  -0.750  -0.0354   0.01438   0.00474  -0.0031   1.0000   1.0000
  -0.500  -0.0162   0.01433   0.00464  -0.0021   1.0000   1.0000
  -0.250   0.0031   0.01431   0.00459  -0.0011   1.0000   1.0000
   0.000   0.0221   0.01433   0.00461   0.0000   1.0000   1.0000
   0.250   0.0403   0.01441   0.00471   0.0011   1.0000   1.0000
   0.500   0.0567   0.01456   0.00491   0.0022   1.0000   1.0000
   0.750   0.0693   0.01486   0.00526   0.0034   1.0000   1.0000
   1.000   0.0771   0.01542   0.00583   0.0047   1.0000   1.0000
   1.250   0.1192   0.01628   0.00678  -0.0013   0.9797   1.0000
   1.500   0.2446   0.01654   0.00740  -0.0194   0.9095   1.0000
   1.750   0.3000   0.01671   0.00760  -0.0225   0.8419   1.0000
   2.000   0.3235   0.01716   0.00791  -0.0198   0.7859   1.0000
   2.250   0.3429   0.01769   0.00828  -0.0165   0.7370   1.0000
   2.500   0.3627   0.01827   0.00875  -0.0137   0.6916   1.0000
   2.750   0.3835   0.01887   0.00921  -0.0112   0.6498   1.0000
   3.000   0.4047   0.01947   0.00966  -0.0089   0.6111   1.0000
   3.250   0.4271   0.02012   0.01024  -0.0072   0.5722   1.0000
   3.500   0.4499   0.02079   0.01082  -0.0054   0.5372   1.0000
   3.750   0.4733   0.02155   0.01154  -0.0040   0.5023   1.0000
   4.000   0.4967   0.02232   0.01224  -0.0026   0.4704   1.0000
   4.250   0.5203   0.02315   0.01303  -0.0013   0.4401   1.0000
   4.500   0.5441   0.02407   0.01392  -0.0001   0.4110   1.0000
   4.750   0.5678   0.02502   0.01485   0.0011   0.3824   1.0000
   5.000   0.5916   0.02608   0.01596   0.0021   0.3550   1.0000
   5.250   0.6152   0.02728   0.01725   0.0030   0.3288   1.0000
   5.500   0.6385   0.02851   0.01857   0.0040   0.3036   1.0000
   5.750   0.6623   0.02986   0.01991   0.0050   0.2823   1.0000
   6.000   0.6846   0.03150   0.02180   0.0057   0.2589   1.0000
   6.250   0.7078   0.03324   0.02362   0.0066   0.2408   1.0000
   6.500   0.7292   0.03528   0.02587   0.0074   0.2223   1.0000
   6.750   0.7492   0.03781   0.02879   0.0079   0.2063   1.0000
   7.000   0.7683   0.04056   0.03184   0.0084   0.1927   1.0000
   7.250   0.7861   0.04323   0.03477   0.0089   0.1789   1.0000
   7.500   0.8009   0.04718   0.03911   0.0089   0.1713   1.0000
   7.750   0.8091   0.05236   0.04472   0.0082   0.1663   1.0000
   8.000   0.8051   0.05930   0.05217   0.0056   0.1640   1.0000
   8.250   0.7960   0.06672   0.05985   0.0020   0.1643   1.0000
   8.500   0.7844   0.07423   0.06747  -0.0023   0.1660   1.0000
   8.750   0.7776   0.08099   0.07426  -0.0058   0.1677   1.0000
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