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S8066 (10% version of S8065 w/ lower surface aerodynamically similar) (s8066-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S8066 (10% version of S8065 w/ lower surface aerodynamically similar) (s8066-il)
Reynolds number: 1,000,000
Max Cl/Cd: 81.22 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8066-il-1000000.txt
Download as CSV file: xf-s8066-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8066 (10% version of S8065 w/ lower surface aer
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.4637   0.14895   0.14744   0.0031   1.0000   0.0091
 -14.250  -0.4615   0.14583   0.14432   0.0011   1.0000   0.0092
  -9.750  -0.8072   0.03374   0.03085  -0.0442   1.0000   0.0066
  -9.500  -0.8046   0.03186   0.02877  -0.0414   1.0000   0.0065
  -9.250  -0.7954   0.02843   0.02499  -0.0409   0.9943   0.0064
  -9.000  -0.7798   0.02400   0.02007  -0.0416   0.9881   0.0066
  -8.750  -0.7546   0.02151   0.01729  -0.0427   0.9843   0.0066
  -8.500  -0.7301   0.01943   0.01496  -0.0432   0.9790   0.0067
  -8.250  -0.7042   0.01784   0.01316  -0.0437   0.9737   0.0067
  -8.000  -0.6794   0.01654   0.01171  -0.0437   0.9681   0.0069
  -7.750  -0.6574   0.01546   0.01048  -0.0430   0.9612   0.0069
  -7.500  -0.6353   0.01453   0.00942  -0.0421   0.9553   0.0070
  -7.250  -0.6139   0.01375   0.00856  -0.0411   0.9492   0.0072
  -7.000  -0.5916   0.01313   0.00785  -0.0402   0.9439   0.0074
  -6.750  -0.5685   0.01257   0.00721  -0.0395   0.9392   0.0077
  -6.500  -0.5457   0.01193   0.00649  -0.0387   0.9343   0.0078
  -6.250  -0.5228   0.01136   0.00581  -0.0378   0.9299   0.0079
  -6.000  -0.4988   0.01083   0.00521  -0.0371   0.9258   0.0082
  -5.750  -0.4742   0.01039   0.00470  -0.0366   0.9215   0.0085
  -5.500  -0.4493   0.01001   0.00424  -0.0360   0.9176   0.0090
  -5.250  -0.4247   0.00957   0.00371  -0.0354   0.9138   0.0104
  -5.000  -0.3988   0.00925   0.00337  -0.0351   0.9099   0.0125
  -4.750  -0.3739   0.00881   0.00300  -0.0346   0.9059   0.0280
  -4.500  -0.3485   0.00849   0.00275  -0.0342   0.9022   0.0468
  -4.250  -0.3227   0.00820   0.00255  -0.0339   0.8985   0.0695
  -4.000  -0.2967   0.00791   0.00236  -0.0337   0.8945   0.0970
  -3.750  -0.2711   0.00757   0.00217  -0.0334   0.8904   0.1355
  -3.500  -0.2459   0.00721   0.00198  -0.0331   0.8866   0.1874
  -3.250  -0.2208   0.00678   0.00180  -0.0328   0.8825   0.2577
  -3.000  -0.1967   0.00624   0.00162  -0.0324   0.8780   0.3570
  -2.750  -0.1718   0.00583   0.00148  -0.0320   0.8739   0.4421
  -2.500  -0.1462   0.00553   0.00139  -0.0317   0.8698   0.5118
  -2.250  -0.1200   0.00529   0.00131  -0.0315   0.8651   0.5630
  -2.000  -0.0932   0.00513   0.00124  -0.0312   0.8606   0.6003
  -1.750  -0.0667   0.00498   0.00119  -0.0310   0.8562   0.6415
  -1.500  -0.0398   0.00485   0.00117  -0.0307   0.8510   0.6783
  -1.250  -0.0126   0.00478   0.00115  -0.0305   0.8459   0.7066
  -1.000   0.0150   0.00474   0.00113  -0.0304   0.8406   0.7279
  -0.750   0.0425   0.00469   0.00112  -0.0303   0.8341   0.7449
  -0.500   0.0701   0.00467   0.00109  -0.0301   0.8278   0.7592
  -0.250   0.0978   0.00464   0.00108  -0.0300   0.8198   0.7727
   0.000   0.1253   0.00463   0.00107  -0.0299   0.8119   0.7853
   0.250   0.1529   0.00460   0.00106  -0.0297   0.8022   0.7965
   0.500   0.1804   0.00458   0.00105  -0.0296   0.7913   0.8061
   0.750   0.2079   0.00459   0.00104  -0.0294   0.7790   0.8150
   1.000   0.2352   0.00459   0.00104  -0.0292   0.7644   0.8229
   1.250   0.2624   0.00463   0.00104  -0.0290   0.7472   0.8303
   1.500   0.2893   0.00468   0.00106  -0.0288   0.7280   0.8378
   1.750   0.3159   0.00476   0.00108  -0.0285   0.7040   0.8451
   2.000   0.3422   0.00486   0.00112  -0.0281   0.6772   0.8527
   2.250   0.3685   0.00497   0.00118  -0.0278   0.6500   0.8600
   2.500   0.3945   0.00510   0.00124  -0.0274   0.6206   0.8679
   2.750   0.4204   0.00524   0.00132  -0.0270   0.5907   0.8756
   3.000   0.4451   0.00548   0.00143  -0.0264   0.5447   0.8844
   3.250   0.4683   0.00581   0.00156  -0.0256   0.4804   0.8935
   3.500   0.4909   0.00622   0.00173  -0.0247   0.4082   0.9038
   3.750   0.5123   0.00672   0.00195  -0.0237   0.3288   0.9161
   4.000   0.5339   0.00719   0.00219  -0.0226   0.2592   0.9305
   4.250   0.5568   0.00762   0.00242  -0.0218   0.2017   0.9471
   4.500   0.5844   0.00807   0.00268  -0.0220   0.1514   0.9631
   4.750   0.6159   0.00856   0.00297  -0.0233   0.1069   0.9759
   5.000   0.6489   0.00897   0.00326  -0.0248   0.0772   0.9861
   5.250   0.6832   0.00933   0.00353  -0.0265   0.0596   0.9935
   5.750   0.7452   0.00995   0.00408  -0.0285   0.0409   1.0000
   6.000   0.7667   0.01023   0.00433  -0.0274   0.0357   1.0000
   6.250   0.7889   0.01051   0.00461  -0.0264   0.0309   1.0000
   6.500   0.8117   0.01078   0.00486  -0.0256   0.0265   1.0000
   6.750   0.8346   0.01111   0.00517  -0.0248   0.0208   1.0000
   7.000   0.8564   0.01157   0.00559  -0.0238   0.0140   1.0000
   7.250   0.8781   0.01210   0.00613  -0.0228   0.0113   1.0000
   7.500   0.9008   0.01250   0.00658  -0.0220   0.0104   1.0000
   7.750   0.9233   0.01296   0.00707  -0.0212   0.0097   1.0000
   8.000   0.9450   0.01349   0.00764  -0.0202   0.0089   1.0000
   8.250   0.9626   0.01449   0.00876  -0.0186   0.0081   1.0000
   8.500   0.9830   0.01516   0.00951  -0.0175   0.0079   1.0000
   8.750   1.0038   0.01579   0.01023  -0.0164   0.0077   1.0000
   9.000   1.0247   0.01637   0.01088  -0.0155   0.0073   1.0000
   9.250   1.0445   0.01708   0.01166  -0.0143   0.0070   1.0000
   9.500   1.0636   0.01783   0.01249  -0.0131   0.0068   1.0000
   9.750   1.0811   0.01873   0.01350  -0.0117   0.0066   1.0000
  10.000   1.0988   0.01957   0.01442  -0.0104   0.0064   1.0000
  10.250   1.1148   0.02058   0.01553  -0.0088   0.0062   1.0000
  10.500   1.1298   0.02161   0.01667  -0.0071   0.0061   1.0000
  10.750   1.1431   0.02275   0.01793  -0.0053   0.0060   1.0000
  11.000   1.1524   0.02406   0.01938  -0.0028   0.0059   1.0000
  11.250   1.1590   0.02536   0.02082  -0.0001   0.0058   1.0000
  11.500   1.1619   0.02701   0.02262   0.0030   0.0057   1.0000
  11.750   1.1538   0.02976   0.02564   0.0069   0.0055   1.0000
  12.000   1.1483   0.03221   0.02831   0.0100   0.0055   1.0000
  12.250   1.1330   0.03561   0.03199   0.0134   0.0054   1.0000
  12.500   1.1378   0.03697   0.03344   0.0149   0.0055   1.0000
  12.750   1.1251   0.04025   0.03693   0.0169   0.0055   1.0000
  13.000   1.1019   0.04484   0.04179   0.0183   0.0054   1.0000
  13.250   1.0797   0.04981   0.04699   0.0183   0.0054   1.0000
  13.500   1.0582   0.05534   0.05272   0.0169   0.0054   1.0000
  13.750   1.0383   0.06140   0.05895   0.0142   0.0054   1.0000
  14.000   1.0293   0.06647   0.06414   0.0114   0.0054   1.0000
  14.250   1.0216   0.07182   0.06959   0.0080   0.0054   1.0000
  14.500   0.9886   0.08346   0.08144   0.0001   0.0054   1.0000
  14.750   0.9708   0.09296   0.09106  -0.0062   0.0054   1.0000
  15.000   0.9545   0.10259   0.10079  -0.0121   0.0054   1.0000
  15.250   0.9329   0.11372   0.11201  -0.0184   0.0054   1.0000
  15.500   0.9421   0.11681   0.11513  -0.0199   0.0057   1.0000
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