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S6061 9% (s6061-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S6061 9% (s6061-il)
Reynolds number: 50,000
Max Cl/Cd: 34.08 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s6061-il-50000.txt
Download as CSV file: xf-s6061-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4598   0.09572   0.08922  -0.0036   1.0000   0.2832
  -7.750  -0.4648   0.09333   0.08693  -0.0038   1.0000   0.3002
  -7.500  -0.4668   0.09063   0.08429  -0.0036   1.0000   0.3150
  -6.250  -0.4985   0.05911   0.05236  -0.0370   1.0000   0.1464
  -6.000  -0.4848   0.05357   0.04668  -0.0370   1.0000   0.1288
  -5.750  -0.4763   0.04844   0.04102  -0.0374   1.0000   0.1160
  -5.500  -0.4642   0.04465   0.03698  -0.0365   1.0000   0.1129
  -5.250  -0.4511   0.04061   0.03238  -0.0355   1.0000   0.1083
  -5.000  -0.4345   0.03737   0.02827  -0.0341   1.0000   0.1041
  -4.750  -0.4161   0.03433   0.02484  -0.0327   1.0000   0.1036
  -4.500  -0.3959   0.03171   0.02166  -0.0311   1.0000   0.1045
  -4.250  -0.3763   0.02934   0.01931  -0.0299   1.0000   0.1112
  -4.000  -0.3549   0.02732   0.01699  -0.0285   1.0000   0.1219
  -3.750  -0.3326   0.02540   0.01496  -0.0270   1.0000   0.1365
  -3.500  -0.3110   0.02362   0.01326  -0.0254   1.0000   0.1700
  -3.250  -0.2894   0.02152   0.01162  -0.0239   1.0000   0.2482
  -3.000  -0.2771   0.01837   0.01036  -0.0205   1.0000   0.4915
  -2.750  -0.1027   0.01793   0.00995  -0.0351   1.0000   1.0000
  -2.500  -0.1154   0.01763   0.00955  -0.0304   1.0000   1.0000
  -2.250  -0.1253   0.01743   0.00922  -0.0259   1.0000   1.0000
  -2.000  -0.1288   0.01731   0.00887  -0.0220   1.0000   1.0000
  -1.750  -0.1257   0.01729   0.00861  -0.0191   1.0000   1.0000
  -1.500  -0.1167   0.01736   0.00842  -0.0171   1.0000   1.0000
  -1.250  -0.1041   0.01749   0.00831  -0.0156   1.0000   1.0000
  -1.000  -0.0894   0.01768   0.00826  -0.0144   1.0000   1.0000
  -0.750  -0.0735   0.01792   0.00828  -0.0135   1.0000   1.0000
  -0.500  -0.0568   0.01820   0.00835  -0.0127   1.0000   1.0000
  -0.250  -0.0397   0.01854   0.00850  -0.0121   1.0000   1.0000
   0.000  -0.0223   0.01891   0.00872  -0.0116   1.0000   1.0000
   0.250  -0.0047   0.01934   0.00900  -0.0111   1.0000   1.0000
   0.500   0.0129   0.01980   0.00935  -0.0108   1.0000   1.0000
   0.750   0.0305   0.02032   0.00974  -0.0105   1.0000   1.0000
   1.000   0.0480   0.02089   0.01022  -0.0103   1.0000   1.0000
   1.250   0.0671   0.02153   0.01078  -0.0105   0.9992   1.0000
   1.500   0.1221   0.02288   0.01208  -0.0173   0.9833   1.0000
   1.750   0.1701   0.02397   0.01315  -0.0227   0.9659   1.0000
   2.000   0.2177   0.02503   0.01422  -0.0278   0.9481   1.0000
   2.250   0.2679   0.02606   0.01532  -0.0330   0.9301   1.0000
   2.500   0.3103   0.02692   0.01624  -0.0367   0.9109   1.0000
   2.750   0.3534   0.02770   0.01712  -0.0401   0.8910   1.0000
   3.000   0.4038   0.02838   0.01795  -0.0444   0.8715   1.0000
   3.250   0.4400   0.02897   0.01871  -0.0461   0.8496   1.0000
   3.500   0.4960   0.02924   0.01921  -0.0504   0.8290   1.0000
   3.750   0.5321   0.02958   0.01973  -0.0514   0.8057   1.0000
   4.000   0.5736   0.02962   0.02005  -0.0524   0.7832   1.0000
   4.250   0.6172   0.02929   0.01997  -0.0529   0.7605   1.0000
   4.500   0.6492   0.02915   0.02004  -0.0518   0.7350   1.0000
   4.750   0.6825   0.02873   0.01989  -0.0503   0.7091   1.0000
   5.000   0.7150   0.02813   0.01952  -0.0482   0.6817   1.0000
   5.250   0.7456   0.02746   0.01904  -0.0456   0.6522   1.0000
   5.500   0.7758   0.02665   0.01842  -0.0427   0.6202   1.0000
   5.750   0.8008   0.02622   0.01811  -0.0395   0.5827   1.0000
   6.000   0.8255   0.02578   0.01771  -0.0363   0.5411   1.0000
   6.250   0.8486   0.02545   0.01732  -0.0329   0.4933   1.0000
   6.500   0.8676   0.02546   0.01716  -0.0295   0.4371   1.0000
   6.750   0.8821   0.02596   0.01744  -0.0260   0.3709   1.0000
   7.000   0.8909   0.02707   0.01800  -0.0223   0.2928   1.0000
   7.250   0.8936   0.02890   0.01917  -0.0187   0.2124   1.0000
   7.500   0.9054   0.03168   0.02144  -0.0163   0.1546   1.0000
   7.750   0.9296   0.03467   0.02427  -0.0151   0.1274   1.0000
   8.000   0.9519   0.03734   0.02708  -0.0140   0.1118   1.0000
   8.250   0.9776   0.04062   0.03033  -0.0135   0.1030   1.0000
   8.500   0.9956   0.04414   0.03453  -0.0119   0.0997   1.0000
   8.750   1.0098   0.04806   0.03907  -0.0104   0.0977   1.0000
   9.000   1.0188   0.05216   0.04369  -0.0089   0.0965   1.0000
   9.250   1.0236   0.05624   0.04820  -0.0073   0.0950   1.0000
   9.500   1.0417   0.06032   0.05215  -0.0070   0.0905   1.0000
   9.750   1.0400   0.06491   0.05712  -0.0056   0.0902   1.0000
  10.000   0.9995   0.06985   0.06295  -0.0033   0.0952   1.0000
  10.250   0.9733   0.07483   0.06817  -0.0025   0.0974   1.0000
  10.500   0.9493   0.07997   0.07343  -0.0029   0.0995   1.0000
  10.750   0.9293   0.08569   0.07922  -0.0047   0.1011   1.0000
  11.000   0.9167   0.09173   0.08529  -0.0069   0.1024   1.0000
  11.250   0.9090   0.09793   0.09154  -0.0091   0.1034   1.0000
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