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S6061 9% (s6061-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S6061 9% (s6061-il)
Reynolds number: 100,000
Max Cl/Cd: 50.11 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s6061-il-100000-n5.txt
Download as CSV file: xf-s6061-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6061 9%                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5007   0.08868   0.08382  -0.0194   1.0000   0.0205
  -8.750  -0.5024   0.08398   0.07919  -0.0221   1.0000   0.0201
  -8.500  -0.5057   0.07898   0.07425  -0.0253   1.0000   0.0196
  -8.250  -0.5116   0.07345   0.06879  -0.0298   1.0000   0.0194
  -8.000  -0.5201   0.06744   0.06279  -0.0348   1.0000   0.0189
  -7.750  -0.5267   0.06114   0.05641  -0.0385   1.0000   0.0184
  -7.500  -0.5315   0.05504   0.05011  -0.0406   1.0000   0.0178
  -7.250  -0.5342   0.04910   0.04385  -0.0415   1.0000   0.0173
  -7.000  -0.5341   0.04339   0.03769  -0.0412   1.0000   0.0168
  -6.750  -0.5268   0.03980   0.03369  -0.0402   1.0000   0.0169
  -6.500  -0.5159   0.03749   0.03118  -0.0390   1.0000   0.0176
  -6.250  -0.5044   0.03520   0.02863  -0.0375   1.0000   0.0185
  -6.000  -0.4923   0.03280   0.02587  -0.0358   1.0000   0.0195
  -5.750  -0.4791   0.03040   0.02306  -0.0339   1.0000   0.0201
  -5.500  -0.4643   0.02803   0.02027  -0.0320   1.0000   0.0205
  -5.250  -0.4479   0.02596   0.01782  -0.0301   1.0000   0.0209
  -5.000  -0.4302   0.02420   0.01575  -0.0284   1.0000   0.0213
  -4.750  -0.3993   0.02236   0.01359  -0.0291   0.9954   0.0222
  -4.500  -0.3664   0.02059   0.01162  -0.0304   0.9890   0.0235
  -4.250  -0.3314   0.01938   0.01033  -0.0322   0.9832   0.0269
  -4.000  -0.2985   0.01835   0.00917  -0.0335   0.9758   0.0328
  -3.750  -0.2622   0.01726   0.00794  -0.0353   0.9702   0.0436
  -3.500  -0.2312   0.01605   0.00706  -0.0364   0.9623   0.0951
  -3.250  -0.1969   0.01490   0.00651  -0.0385   0.9567   0.2178
  -3.000  -0.1681   0.01407   0.00616  -0.0392   0.9478   0.3421
  -2.750  -0.1383   0.01327   0.00595  -0.0398   0.9406   0.4949
  -2.500  -0.1112   0.01277   0.00591  -0.0391   0.9320   0.6362
  -2.250  -0.0842   0.01258   0.00589  -0.0379   0.9235   0.7345
  -2.000  -0.0543   0.01251   0.00584  -0.0373   0.9159   0.8024
  -1.750  -0.0255   0.01249   0.00578  -0.0366   0.9065   0.8508
  -1.500   0.0101   0.01247   0.00566  -0.0374   0.8995   0.8901
  -1.250   0.0486   0.01245   0.00550  -0.0389   0.8910   0.9214
  -1.000   0.0925   0.01240   0.00532  -0.0418   0.8836   0.9467
  -0.750   0.1381   0.01233   0.00512  -0.0451   0.8754   0.9676
  -0.500   0.1862   0.01223   0.00489  -0.0492   0.8663   0.9845
  -0.250   0.2326   0.01209   0.00464  -0.0530   0.8570   1.0000
   0.000   0.2542   0.01208   0.00454  -0.0519   0.8437   1.0000
   0.250   0.2757   0.01208   0.00445  -0.0506   0.8302   1.0000
   0.500   0.2973   0.01209   0.00439  -0.0494   0.8166   1.0000
   0.750   0.3191   0.01212   0.00435  -0.0481   0.8028   1.0000
   1.000   0.3413   0.01216   0.00434  -0.0469   0.7889   1.0000
   1.250   0.3638   0.01221   0.00434  -0.0458   0.7749   1.0000
   1.500   0.3867   0.01227   0.00435  -0.0447   0.7608   1.0000
   1.750   0.4099   0.01234   0.00438  -0.0436   0.7463   1.0000
   2.000   0.4335   0.01242   0.00443  -0.0426   0.7311   1.0000
   2.250   0.4574   0.01251   0.00452  -0.0417   0.7151   1.0000
   2.500   0.4815   0.01261   0.00460  -0.0408   0.6986   1.0000
   2.750   0.5059   0.01272   0.00470  -0.0399   0.6818   1.0000
   3.000   0.5305   0.01284   0.00480  -0.0391   0.6645   1.0000
   3.250   0.5551   0.01297   0.00495  -0.0383   0.6462   1.0000
   3.500   0.5797   0.01312   0.00511  -0.0375   0.6258   1.0000
   3.750   0.6043   0.01329   0.00526  -0.0366   0.6047   1.0000
   4.000   0.6287   0.01347   0.00546  -0.0358   0.5813   1.0000
   4.250   0.6531   0.01369   0.00572  -0.0350   0.5565   1.0000
   4.500   0.6773   0.01393   0.00596  -0.0342   0.5296   1.0000
   4.750   0.7012   0.01421   0.00623  -0.0334   0.4998   1.0000
   5.000   0.7246   0.01453   0.00652  -0.0324   0.4670   1.0000
   5.250   0.7477   0.01492   0.00691  -0.0316   0.4308   1.0000
   5.500   0.7701   0.01538   0.00730  -0.0306   0.3917   1.0000
   5.750   0.7918   0.01594   0.00776  -0.0296   0.3492   1.0000
   6.000   0.8117   0.01668   0.00827  -0.0285   0.2940   1.0000
   6.250   0.8304   0.01760   0.00888  -0.0274   0.2315   1.0000
   6.500   0.8485   0.01866   0.00960  -0.0265   0.1665   1.0000
   6.750   0.8659   0.01990   0.01047  -0.0254   0.1069   1.0000
   7.000   0.8836   0.02118   0.01159  -0.0243   0.0658   1.0000
   7.250   0.9002   0.02262   0.01291  -0.0230   0.0463   1.0000
   7.500   0.9180   0.02386   0.01427  -0.0217   0.0391   1.0000
   7.750   0.9335   0.02530   0.01579  -0.0202   0.0352   1.0000
   8.000   0.9492   0.02669   0.01734  -0.0187   0.0331   1.0000
   8.250   0.9659   0.02798   0.01881  -0.0173   0.0305   1.0000
   8.500   0.9821   0.02929   0.02023  -0.0161   0.0279   1.0000
   8.750   0.9966   0.03086   0.02190  -0.0147   0.0263   1.0000
   9.000   1.0104   0.03299   0.02416  -0.0133   0.0252   1.0000
   9.250   1.0276   0.03497   0.02633  -0.0121   0.0245   1.0000
   9.500   1.0447   0.03715   0.02878  -0.0110   0.0239   1.0000
   9.750   1.0600   0.03962   0.03155  -0.0097   0.0233   1.0000
  10.000   1.0718   0.04225   0.03453  -0.0083   0.0226   1.0000
  10.250   1.0793   0.04469   0.03730  -0.0067   0.0215   1.0000
  10.500   1.0830   0.04697   0.03985  -0.0049   0.0204   1.0000
  10.750   1.0818   0.04944   0.04257  -0.0028   0.0197   1.0000
  11.000   1.0771   0.05228   0.04567  -0.0010   0.0194   1.0000
  11.250   1.0692   0.05548   0.04913   0.0004   0.0192   1.0000
  11.500   1.0582   0.05914   0.05306   0.0012   0.0191   1.0000
  11.750   1.0453   0.06312   0.05727   0.0010   0.0189   1.0000
  12.000   1.0289   0.06792   0.06233  -0.0001   0.0190   1.0000
  12.250   1.0108   0.07337   0.06801  -0.0023   0.0190   1.0000
  12.500   0.9898   0.07993   0.07480  -0.0060   0.0192   1.0000
  12.750   0.9654   0.08802   0.08309  -0.0113   0.0194   1.0000
  13.000   0.9339   0.09903   0.09430  -0.0191   0.0199   1.0000
  13.250   0.8944   0.11470   0.11008  -0.0298   0.0210   1.0000
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