Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S8025 (8%) (s8025-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S8025 (8%) (s8025-il)
Reynolds number: 1,000,000
Max Cl/Cd: 77.99 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s8025-il-1000000-n5.txt
Download as CSV file: xf-s8025-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.8858   0.08045   0.07867   0.0123   1.0000   0.0022
 -11.750  -0.9282   0.06634   0.06448   0.0039   1.0000   0.0022
 -11.500  -0.9597   0.05168   0.04964  -0.0080   1.0000   0.0022
 -11.250  -0.9784   0.04397   0.04176  -0.0159   1.0000   0.0022
 -11.000  -1.0058   0.03941   0.03700  -0.0160   1.0000   0.0022
 -10.750  -1.0135   0.03576   0.03309  -0.0153   1.0000   0.0022
 -10.500  -1.0136   0.03235   0.02940  -0.0145   1.0000   0.0022
 -10.250  -1.0071   0.02943   0.02619  -0.0136   1.0000   0.0022
 -10.000  -0.9967   0.02679   0.02327  -0.0127   1.0000   0.0022
  -9.750  -0.9817   0.02474   0.02097  -0.0118   1.0000   0.0022
  -9.500  -0.9649   0.02281   0.01880  -0.0110   1.0000   0.0022
  -9.250  -0.9461   0.02117   0.01693  -0.0102   1.0000   0.0022
  -9.000  -0.9260   0.01971   0.01527  -0.0095   1.0000   0.0022
  -8.750  -0.9046   0.01845   0.01383  -0.0088   1.0000   0.0022
  -8.500  -0.8825   0.01729   0.01252  -0.0081   1.0000   0.0022
  -8.250  -0.8595   0.01630   0.01139  -0.0075   1.0000   0.0022
  -8.000  -0.8360   0.01539   0.01035  -0.0070   1.0000   0.0023
  -7.750  -0.8119   0.01458   0.00943  -0.0064   1.0000   0.0023
  -7.500  -0.7874   0.01386   0.00862  -0.0059   1.0000   0.0023
  -7.250  -0.7625   0.01319   0.00785  -0.0054   1.0000   0.0023
  -7.000  -0.7373   0.01261   0.00719  -0.0050   1.0000   0.0024
  -6.750  -0.7123   0.01192   0.00641  -0.0044   1.0000   0.0025
  -6.500  -0.6872   0.01126   0.00566  -0.0039   1.0000   0.0026
  -6.250  -0.6614   0.01076   0.00511  -0.0035   1.0000   0.0029
  -6.000  -0.6353   0.01037   0.00467  -0.0031   1.0000   0.0031
  -5.750  -0.6091   0.01002   0.00429  -0.0027   1.0000   0.0035
  -5.500  -0.5827   0.00970   0.00394  -0.0023   1.0000   0.0038
  -5.250  -0.5562   0.00942   0.00362  -0.0019   1.0000   0.0041
  -5.000  -0.5299   0.00910   0.00329  -0.0015   1.0000   0.0049
  -4.750  -0.5035   0.00883   0.00300  -0.0011   1.0000   0.0062
  -4.500  -0.4772   0.00854   0.00273  -0.0007   1.0000   0.0100
  -4.250  -0.4507   0.00817   0.00244  -0.0004   0.9992   0.0223
  -4.000  -0.4139   0.00777   0.00218  -0.0024   0.9719   0.0453
  -3.750  -0.3762   0.00759   0.00195  -0.0044   0.8977   0.0654
  -3.250  -0.3278   0.00743   0.00160  -0.0025   0.7737   0.1170
  -3.000  -0.3016   0.00736   0.00146  -0.0021   0.7323   0.1388
  -2.750  -0.2748   0.00731   0.00133  -0.0018   0.6976   0.1565
  -2.500  -0.2477   0.00724   0.00122  -0.0015   0.6678   0.1746
  -2.000  -0.1936   0.00711   0.00103  -0.0010   0.6000   0.2231
  -1.750  -0.1664   0.00708   0.00094  -0.0008   0.5664   0.2460
  -1.500  -0.1392   0.00702   0.00087  -0.0006   0.5357   0.2743
  -1.250  -0.1120   0.00692   0.00081  -0.0005   0.5079   0.3123
  -0.750  -0.0573   0.00677   0.00072  -0.0002   0.4619   0.3813
  -0.250  -0.0026   0.00665   0.00068   0.0002   0.4183   0.4524
   0.000   0.0246   0.00660   0.00067   0.0004   0.3953   0.4949
   0.250   0.0518   0.00657   0.00068   0.0005   0.3678   0.5354
   0.500   0.0790   0.00654   0.00070   0.0007   0.3457   0.5744
   0.750   0.1065   0.00653   0.00072   0.0009   0.3290   0.6050
   1.000   0.1338   0.00653   0.00075   0.0011   0.3111   0.6359
   1.250   0.1612   0.00654   0.00079   0.0013   0.2932   0.6658
   1.500   0.1882   0.00651   0.00084   0.0016   0.2791   0.7045
   1.750   0.2150   0.00648   0.00090   0.0020   0.2654   0.7459
   2.000   0.2415   0.00647   0.00097   0.0024   0.2497   0.7859
   2.250   0.2676   0.00646   0.00104   0.0029   0.2340   0.8269
   2.500   0.2928   0.00647   0.00113   0.0037   0.2134   0.8719
   2.750   0.3181   0.00648   0.00123   0.0045   0.1976   0.9257
   3.250   0.3932   0.00674   0.00143   0.0005   0.1665   0.9905
   3.500   0.4269   0.00691   0.00155  -0.0007   0.1541   1.0000
   3.750   0.4533   0.00706   0.00167  -0.0003   0.1433   1.0000
   4.000   0.4798   0.00722   0.00179   0.0000   0.1334   1.0000
   4.250   0.5063   0.00741   0.00194   0.0004   0.1215   1.0000
   4.500   0.5327   0.00763   0.00210   0.0007   0.1075   1.0000
   4.750   0.5592   0.00786   0.00227   0.0010   0.0953   1.0000
   5.000   0.5857   0.00808   0.00245   0.0013   0.0853   1.0000
   5.250   0.6122   0.00833   0.00266   0.0016   0.0748   1.0000
   5.500   0.6388   0.00857   0.00287   0.0019   0.0654   1.0000
   5.750   0.6654   0.00880   0.00309   0.0022   0.0586   1.0000
   6.000   0.6919   0.00908   0.00334   0.0025   0.0516   1.0000
   6.250   0.7186   0.00931   0.00358   0.0027   0.0472   1.0000
   6.500   0.7449   0.00961   0.00386   0.0030   0.0408   1.0000
   6.750   0.7713   0.00989   0.00414   0.0033   0.0358   1.0000
   7.000   0.7974   0.01025   0.00447   0.0036   0.0291   1.0000
   7.250   0.8235   0.01057   0.00479   0.0039   0.0253   1.0000
   7.500   0.8496   0.01094   0.00517   0.0042   0.0218   1.0000
   7.750   0.8758   0.01124   0.00551   0.0044   0.0205   1.0000
   8.000   0.9018   0.01158   0.00588   0.0047   0.0186   1.0000
   8.250   0.9274   0.01198   0.00628   0.0050   0.0166   1.0000
   8.500   0.9530   0.01238   0.00672   0.0053   0.0150   1.0000
   8.750   0.9788   0.01272   0.00713   0.0056   0.0141   1.0000
   9.000   1.0042   0.01313   0.00756   0.0059   0.0126   1.0000
   9.250   1.0291   0.01360   0.00805   0.0063   0.0109   1.0000
   9.500   1.0543   0.01403   0.00853   0.0066   0.0099   1.0000
   9.750   1.0790   0.01452   0.00906   0.0069   0.0083   1.0000
  10.000   1.1031   0.01510   0.00966   0.0073   0.0067   1.0000
  10.250   1.1268   0.01572   0.01032   0.0077   0.0053   1.0000
  10.500   1.1502   0.01637   0.01105   0.0082   0.0044   1.0000
  10.750   1.1732   0.01705   0.01180   0.0087   0.0038   1.0000
  11.000   1.1956   0.01781   0.01263   0.0092   0.0033   1.0000
  11.250   1.2173   0.01865   0.01356   0.0097   0.0030   1.0000
  11.500   1.2394   0.01938   0.01438   0.0102   0.0028   1.0000
  11.750   1.2606   0.02019   0.01530   0.0108   0.0027   1.0000
  12.000   1.2810   0.02106   0.01627   0.0114   0.0026   1.0000
  12.250   1.3006   0.02200   0.01732   0.0121   0.0024   1.0000
  12.500   1.3191   0.02302   0.01847   0.0128   0.0023   1.0000
  12.750   1.3362   0.02413   0.01969   0.0135   0.0022   1.0000
  13.000   1.3511   0.02541   0.02110   0.0144   0.0021   1.0000
  13.250   1.3644   0.02676   0.02257   0.0154   0.0020   1.0000
  13.500   1.3725   0.02850   0.02447   0.0166   0.0019   1.0000
  13.750   1.3776   0.03029   0.02640   0.0180   0.0018   1.0000
  14.000   1.3716   0.03227   0.02853   0.0205   0.0018   1.0000
  14.250   1.3551   0.03537   0.03179   0.0215   0.0017   1.0000
  14.500   1.3429   0.03954   0.03612   0.0193   0.0017   1.0000
  14.750   1.3206   0.04699   0.04377   0.0135   0.0017   1.0000
  15.000   1.2984   0.05528   0.05224   0.0074   0.0018   1.0000
  15.250   1.2608   0.06631   0.06345   0.0002   0.0018   1.0000
  15.500   1.2299   0.07586   0.07313  -0.0055   0.0019   1.0000
  15.750   1.1852   0.08811   0.08553  -0.0127   0.0020   1.0000
  16.000   1.1413   0.10065   0.09821  -0.0200   0.0021   1.0000
<< Back to S8025 (8%) (s8025-il)

Polar data table (+)

Polar graphs


<< Back to S8025 (8%) (s8025-il)