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S9033 (7.5%) (s9033-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S9033 (7.5%) (s9033-il)
Reynolds number: 500,000
Max Cl/Cd: 56.88 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9033-il-500000.txt
Download as CSV file: xf-s9033-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9033 (7.5%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -1.0921   0.04558   0.04252  -0.0216   1.0000   0.0108
 -12.250  -1.1056   0.04163   0.03840  -0.0233   1.0000   0.0108
 -12.000  -1.1076   0.03981   0.03651  -0.0225   1.0000   0.0112
 -11.750  -1.1064   0.03830   0.03491  -0.0209   1.0000   0.0115
 -11.500  -1.0995   0.03668   0.03314  -0.0200   1.0000   0.0121
 -11.250  -1.0884   0.03534   0.03166  -0.0192   1.0000   0.0128
 -11.000  -1.0723   0.03451   0.03069  -0.0185   1.0000   0.0136
 -10.750  -1.0529   0.03413   0.03018  -0.0179   1.0000   0.0142
 -10.500  -1.0610   0.02866   0.02422  -0.0162   1.0000   0.0152
 -10.250  -1.0413   0.02795   0.02349  -0.0157   1.0000   0.0161
 -10.000  -1.0212   0.02717   0.02262  -0.0151   1.0000   0.0169
  -9.750  -1.0001   0.02644   0.02179  -0.0145   1.0000   0.0180
  -9.500  -0.9792   0.02551   0.02071  -0.0138   1.0000   0.0190
  -9.250  -0.9567   0.02489   0.01992  -0.0133   1.0000   0.0197
  -9.000  -0.9398   0.02260   0.01732  -0.0123   1.0000   0.0206
  -8.750  -0.9222   0.02035   0.01486  -0.0113   1.0000   0.0219
  -8.500  -0.8998   0.01934   0.01375  -0.0107   1.0000   0.0228
  -8.250  -0.8768   0.01841   0.01272  -0.0100   1.0000   0.0237
  -8.000  -0.8531   0.01763   0.01184  -0.0094   1.0000   0.0248
  -7.750  -0.8291   0.01687   0.01098  -0.0088   1.0000   0.0259
  -7.500  -0.8052   0.01603   0.01000  -0.0081   1.0000   0.0267
  -7.250  -0.7809   0.01530   0.00917  -0.0075   1.0000   0.0274
  -7.000  -0.7566   0.01457   0.00834  -0.0068   1.0000   0.0281
  -6.750  -0.7348   0.01325   0.00692  -0.0059   1.0000   0.0305
  -6.500  -0.7098   0.01272   0.00637  -0.0053   1.0000   0.0333
  -6.250  -0.6843   0.01231   0.00589  -0.0048   1.0000   0.0364
  -6.000  -0.6599   0.01160   0.00515  -0.0041   1.0000   0.0418
  -5.750  -0.6341   0.01124   0.00477  -0.0036   1.0000   0.0484
  -5.500  -0.6091   0.01073   0.00429  -0.0031   1.0000   0.0581
  -5.250  -0.5835   0.01036   0.00392  -0.0026   1.0000   0.0664
  -5.000  -0.5576   0.01009   0.00364  -0.0021   1.0000   0.0743
  -4.750  -0.5322   0.00973   0.00333  -0.0016   1.0000   0.0857
  -4.500  -0.5066   0.00942   0.00306  -0.0010   1.0000   0.0992
  -4.250  -0.4812   0.00910   0.00282  -0.0005   1.0000   0.1161
  -4.000  -0.4560   0.00878   0.00261   0.0001   1.0000   0.1386
  -3.750  -0.4308   0.00847   0.00240   0.0006   1.0000   0.1632
  -3.500  -0.4056   0.00819   0.00222   0.0012   1.0000   0.1894
  -3.250  -0.3805   0.00792   0.00206   0.0018   1.0000   0.2168
  -3.000  -0.3555   0.00766   0.00191   0.0024   1.0000   0.2462
  -2.750  -0.3304   0.00741   0.00178   0.0031   1.0000   0.2786
  -2.500  -0.3055   0.00716   0.00167   0.0037   1.0000   0.3148
  -2.250  -0.2809   0.00690   0.00158   0.0044   1.0000   0.3576
  -2.000  -0.2563   0.00664   0.00151   0.0051   1.0000   0.4033
  -1.750  -0.2320   0.00640   0.00145   0.0059   1.0000   0.4514
  -1.500  -0.2081   0.00615   0.00142   0.0067   1.0000   0.5070
  -1.250  -0.1846   0.00590   0.00142   0.0076   1.0000   0.5674
  -1.000  -0.1446   0.00565   0.00143   0.0051   0.9927   0.6319
  -0.750  -0.1028   0.00541   0.00143   0.0022   0.9820   0.6923
  -0.500  -0.0669   0.00516   0.00142   0.0008   0.9631   0.7537
  -0.250  -0.0307   0.00490   0.00141  -0.0004   0.9346   0.8197
   0.000   0.0000   0.00477   0.00141   0.0000   0.8872   0.8871
   0.250   0.0307   0.00490   0.00141   0.0004   0.8198   0.9347
   0.500   0.0669   0.00516   0.00142  -0.0008   0.7534   0.9632
   0.750   0.1028   0.00541   0.00143  -0.0022   0.6926   0.9820
   1.000   0.1446   0.00565   0.00143  -0.0051   0.6320   0.9927
   1.250   0.1846   0.00590   0.00142  -0.0076   0.5671   1.0000
   1.500   0.2082   0.00614   0.00143  -0.0067   0.5076   1.0000
   1.750   0.2321   0.00640   0.00145  -0.0059   0.4510   1.0000
   2.000   0.2565   0.00664   0.00151  -0.0051   0.4031   1.0000
   2.250   0.2810   0.00689   0.00158  -0.0044   0.3579   1.0000
   2.500   0.3057   0.00716   0.00167  -0.0037   0.3148   1.0000
   2.750   0.3306   0.00741   0.00178  -0.0031   0.2787   1.0000
   3.000   0.3556   0.00766   0.00191  -0.0025   0.2462   1.0000
   3.250   0.3807   0.00792   0.00206  -0.0019   0.2167   1.0000
   3.500   0.4058   0.00819   0.00222  -0.0012   0.1893   1.0000
   3.750   0.4309   0.00847   0.00240  -0.0007   0.1631   1.0000
   4.000   0.4561   0.00878   0.00261  -0.0001   0.1384   1.0000
   4.250   0.4813   0.00910   0.00282   0.0005   0.1162   1.0000
   4.500   0.5067   0.00942   0.00307   0.0010   0.0992   1.0000
   4.750   0.5322   0.00973   0.00333   0.0015   0.0857   1.0000
   5.000   0.5577   0.01009   0.00364   0.0021   0.0743   1.0000
   5.250   0.5836   0.01036   0.00392   0.0026   0.0664   1.0000
   5.500   0.6091   0.01073   0.00429   0.0031   0.0581   1.0000
   5.750   0.6341   0.01124   0.00477   0.0036   0.0484   1.0000
   6.000   0.6598   0.01160   0.00515   0.0041   0.0418   1.0000
   6.250   0.6842   0.01230   0.00589   0.0048   0.0364   1.0000
   6.500   0.7098   0.01271   0.00636   0.0053   0.0333   1.0000
   6.750   0.7347   0.01325   0.00692   0.0059   0.0306   1.0000
   7.000   0.7565   0.01456   0.00833   0.0069   0.0281   1.0000
   7.250   0.7808   0.01530   0.00917   0.0075   0.0274   1.0000
   7.500   0.8051   0.01603   0.01000   0.0082   0.0267   1.0000
   7.750   0.8289   0.01686   0.01096   0.0088   0.0259   1.0000
   8.000   0.8529   0.01763   0.01184   0.0095   0.0248   1.0000
   8.250   0.8766   0.01841   0.01272   0.0101   0.0237   1.0000
   8.500   0.8996   0.01934   0.01375   0.0107   0.0228   1.0000
   8.750   0.9220   0.02034   0.01484   0.0114   0.0219   1.0000
   9.000   0.9396   0.02258   0.01730   0.0123   0.0206   1.0000
   9.250   0.9564   0.02489   0.01992   0.0133   0.0197   1.0000
   9.500   0.9790   0.02551   0.02071   0.0139   0.0190   1.0000
   9.750   0.9999   0.02641   0.02176   0.0145   0.0180   1.0000
  10.000   1.0207   0.02720   0.02265   0.0151   0.0170   1.0000
  10.250   1.0408   0.02799   0.02353   0.0157   0.0161   1.0000
  10.500   1.0605   0.02869   0.02426   0.0163   0.0152   1.0000
  10.750   1.0513   0.03432   0.03040   0.0180   0.0142   1.0000
  11.000   1.0712   0.03461   0.03080   0.0186   0.0136   1.0000
  11.250   1.0847   0.03580   0.03216   0.0194   0.0129   1.0000
  11.500   1.0987   0.03671   0.03318   0.0201   0.0121   1.0000
  11.750   1.1070   0.03814   0.03474   0.0210   0.0115   1.0000
  12.000   1.1055   0.03994   0.03665   0.0227   0.0112   1.0000
  12.250   1.1036   0.04177   0.03856   0.0234   0.0109   1.0000
  12.500   1.0918   0.04556   0.04249   0.0216   0.0108   1.0000
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