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S4053 (s4053-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S4053 (s4053-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.98 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4053-il-1000000.txt
Download as CSV file: xf-s4053-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4053                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3079   0.08238   0.08086  -0.0340   1.0000   0.0098
  -9.000  -0.3094   0.07871   0.07720  -0.0344   1.0000   0.0099
  -8.750  -0.3120   0.07499   0.07350  -0.0348   1.0000   0.0100
  -8.500  -0.3158   0.07129   0.06982  -0.0352   1.0000   0.0103
  -8.250  -0.3211   0.06762   0.06617  -0.0353   1.0000   0.0104
  -8.000  -0.3286   0.06411   0.06270  -0.0352   1.0000   0.0105
  -6.000  -0.2718   0.02380   0.02067  -0.0817   0.9578   0.0132
  -5.750  -0.2459   0.02234   0.01909  -0.0823   0.9455   0.0137
  -5.500  -0.2192   0.02091   0.01747  -0.0828   0.9311   0.0146
  -5.250  -0.1941   0.01943   0.01572  -0.0824   0.9135   0.0159
  -5.000  -0.1699   0.00722   0.00340  -0.0762   0.8577   0.0172
  -4.500  -0.1262   0.01258   0.00756  -0.0785   0.8618   0.0128
  -4.250  -0.1005   0.01202   0.00684  -0.0779   0.8476   0.0126
  -4.000  -0.0769   0.01052   0.00516  -0.0769   0.8344   0.0129
  -3.750  -0.0523   0.00974   0.00428  -0.0762   0.8220   0.0133
  -3.500  -0.0269   0.00927   0.00372  -0.0757   0.8104   0.0138
  -3.250  -0.0012   0.00890   0.00327  -0.0752   0.7994   0.0142
  -3.000   0.0248   0.00856   0.00285  -0.0747   0.7888   0.0146
  -2.750   0.0512   0.00830   0.00253  -0.0744   0.7790   0.0153
  -2.500   0.0777   0.00806   0.00221  -0.0740   0.7698   0.0161
  -2.250   0.1044   0.00784   0.00191  -0.0736   0.7607   0.0168
  -2.000   0.1313   0.00762   0.00162  -0.0733   0.7521   0.0179
  -1.500   0.1852   0.00726   0.00119  -0.0728   0.7356   0.0349
  -1.250   0.2096   0.00662   0.00107  -0.0724   0.7278   0.2037
  -1.000   0.2343   0.00608   0.00102  -0.0720   0.7196   0.3706
  -0.750   0.2591   0.00568   0.00100  -0.0716   0.7120   0.5091
  -0.500   0.2839   0.00536   0.00100  -0.0710   0.7037   0.6280
  -0.250   0.3066   0.00498   0.00103  -0.0699   0.6957   0.7689
   0.000   0.3277   0.00463   0.00109  -0.0679   0.6877   0.9165
   0.250   0.3709   0.00466   0.00112  -0.0711   0.6798   0.9722
   0.750   0.4636   0.00477   0.00111  -0.0793   0.6620   0.9976
   1.000   0.4977   0.00481   0.00110  -0.0807   0.6528   1.0000
   1.250   0.5223   0.00488   0.00110  -0.0800   0.6432   1.0000
   1.500   0.5473   0.00493   0.00112  -0.0794   0.6332   1.0000
   1.750   0.5723   0.00499   0.00115  -0.0787   0.6235   1.0000
   2.000   0.5970   0.00507   0.00118  -0.0780   0.6131   1.0000
   2.250   0.6220   0.00515   0.00122  -0.0774   0.6010   1.0000
   2.500   0.6468   0.00524   0.00127  -0.0767   0.5871   1.0000
   2.750   0.6713   0.00535   0.00132  -0.0760   0.5715   1.0000
   3.000   0.6959   0.00546   0.00138  -0.0753   0.5534   1.0000
   3.250   0.7204   0.00560   0.00146  -0.0746   0.5341   1.0000
   3.500   0.7442   0.00577   0.00156  -0.0738   0.5108   1.0000
   3.750   0.7678   0.00598   0.00166  -0.0729   0.4839   1.0000
   4.000   0.7910   0.00623   0.00180  -0.0720   0.4533   1.0000
   4.250   0.8129   0.00658   0.00197  -0.0709   0.4107   1.0000
   4.500   0.8352   0.00694   0.00216  -0.0699   0.3716   1.0000
   4.750   0.8578   0.00729   0.00237  -0.0690   0.3352   1.0000
   5.000   0.8800   0.00768   0.00260  -0.0680   0.2978   1.0000
   5.250   0.9017   0.00813   0.00287  -0.0670   0.2570   1.0000
   5.500   0.9241   0.00853   0.00313  -0.0661   0.2229   1.0000
   5.750   0.9463   0.00896   0.00341  -0.0652   0.1914   1.0000
   6.000   0.9685   0.00939   0.00371  -0.0643   0.1623   1.0000
   6.250   0.9904   0.00984   0.00403  -0.0633   0.1345   1.0000
   6.500   1.0126   0.01027   0.00436  -0.0624   0.1110   1.0000
   6.750   1.0347   0.01071   0.00471  -0.0615   0.0910   1.0000
   7.000   1.0565   0.01116   0.00507  -0.0606   0.0734   1.0000
   7.250   1.0785   0.01159   0.00543  -0.0597   0.0605   1.0000
   7.500   1.1010   0.01198   0.00579  -0.0589   0.0513   1.0000
   7.750   1.1232   0.01238   0.00619  -0.0580   0.0443   1.0000
   8.000   1.1455   0.01276   0.00656  -0.0572   0.0395   1.0000
   8.250   1.1673   0.01319   0.00699  -0.0563   0.0346   1.0000
   8.500   1.1898   0.01352   0.00734  -0.0555   0.0315   1.0000
   8.750   1.2098   0.01406   0.00786  -0.0543   0.0263   1.0000
   9.000   1.2324   0.01436   0.00821  -0.0536   0.0239   1.0000
   9.250   1.2516   0.01493   0.00875  -0.0523   0.0189   1.0000
   9.500   1.2709   0.01546   0.00927  -0.0511   0.0148   1.0000
   9.750   1.2894   0.01605   0.00988  -0.0497   0.0122   1.0000
  10.000   1.3059   0.01675   0.01060  -0.0480   0.0102   1.0000
  10.250   1.3224   0.01742   0.01134  -0.0463   0.0092   1.0000
  10.500   1.3389   0.01802   0.01200  -0.0446   0.0085   1.0000
  10.750   1.3525   0.01866   0.01271  -0.0424   0.0078   1.0000
  11.000   1.3623   0.01948   0.01360  -0.0397   0.0072   1.0000
  11.250   1.3653   0.02075   0.01499  -0.0360   0.0066   1.0000
  11.500   1.3774   0.02145   0.01577  -0.0339   0.0064   1.0000
  11.750   1.3879   0.02228   0.01668  -0.0317   0.0062   1.0000
  12.000   1.3958   0.02330   0.01780  -0.0293   0.0060   1.0000
  12.250   1.4050   0.02427   0.01885  -0.0272   0.0057   1.0000
  12.500   1.4129   0.02537   0.02003  -0.0251   0.0054   1.0000
  12.750   1.4175   0.02675   0.02152  -0.0229   0.0054   1.0000
  13.000   1.4232   0.02812   0.02297  -0.0211   0.0051   1.0000
  13.250   1.4256   0.02982   0.02479  -0.0192   0.0050   1.0000
  13.500   1.4234   0.03201   0.02709  -0.0174   0.0047   1.0000
  13.750   1.4139   0.03504   0.03028  -0.0155   0.0045   1.0000
  14.000   1.4033   0.03839   0.03380  -0.0141   0.0044   1.0000
  14.250   1.4025   0.04095   0.03650  -0.0133   0.0043   1.0000
  14.500   1.4095   0.04275   0.03839  -0.0130   0.0042   1.0000
  14.750   1.4060   0.04581   0.04157  -0.0128   0.0042   1.0000
  15.000   1.3986   0.04946   0.04536  -0.0128   0.0042   1.0000
  15.250   1.3971   0.05256   0.04858  -0.0131   0.0041   1.0000
  15.500   1.3890   0.05669   0.05286  -0.0139   0.0040   1.0000
  15.750   1.3780   0.06147   0.05779  -0.0151   0.0040   1.0000
  16.000   1.3720   0.06577   0.06221  -0.0165   0.0039   1.0000
  16.250   1.3619   0.07093   0.06750  -0.0185   0.0039   1.0000
  16.500   1.3496   0.07674   0.07346  -0.0209   0.0039   1.0000
  16.750   1.3338   0.08349   0.08036  -0.0241   0.0038   1.0000
  17.000   1.3170   0.09074   0.08777  -0.0277   0.0039   1.0000
  17.250   1.3033   0.09774   0.09489  -0.0314   0.0038   1.0000
  17.500   1.2873   0.10546   0.10276  -0.0356   0.0038   1.0000
  17.750   1.2654   0.11467   0.11212  -0.0407   0.0038   1.0000
  18.000   1.2464   0.12348   0.12107  -0.0457   0.0039   1.0000
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