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S4053 (s4053-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S4053 (s4053-il)
Reynolds number: 500,000
Max Cl/Cd: 96.46 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4053-il-500000-n5.txt
Download as CSV file: xf-s4053-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3164   0.07571   0.07361  -0.0356   1.0000   0.0105
  -8.250  -0.3997   0.08065   0.07846  -0.0342   1.0000   0.0105
  -8.000  -0.4077   0.07735   0.07521  -0.0344   1.0000   0.0099
  -7.750  -0.4164   0.07364   0.07154  -0.0358   0.9988   0.0096
  -7.500  -0.4010   0.06536   0.06325  -0.0481   0.9903   0.0092
  -7.250  -0.3849   0.05423   0.05198  -0.0620   0.9803   0.0086
  -6.750  -0.3492   0.03809   0.03528  -0.0744   0.9583   0.0088
  -6.500  -0.3301   0.03087   0.02758  -0.0771   0.9458   0.0088
  -6.250  -0.3068   0.02580   0.02201  -0.0786   0.9336   0.0090
  -6.000  -0.2799   0.02314   0.01900  -0.0796   0.9212   0.0094
  -5.750  -0.2537   0.02094   0.01643  -0.0800   0.9070   0.0099
  -5.500  -0.2294   0.01870   0.01377  -0.0796   0.8915   0.0099
  -5.250  -0.2054   0.01686   0.01153  -0.0790   0.8765   0.0099
  -5.000  -0.1810   0.01542   0.00977  -0.0783   0.8622   0.0098
  -4.750  -0.1563   0.01427   0.00837  -0.0776   0.8487   0.0100
  -4.500  -0.1313   0.01334   0.00723  -0.0769   0.8361   0.0101
  -4.250  -0.1061   0.01256   0.00628  -0.0763   0.8242   0.0104
  -4.000  -0.0808   0.01193   0.00550  -0.0757   0.8131   0.0108
  -3.750  -0.0553   0.01142   0.00485  -0.0752   0.8025   0.0112
  -3.500  -0.0295   0.01100   0.00433  -0.0747   0.7921   0.0116
  -3.250  -0.0034   0.01067   0.00392  -0.0743   0.7824   0.0119
  -3.000   0.0218   0.01014   0.00328  -0.0737   0.7732   0.0124
  -2.750   0.0477   0.00977   0.00283  -0.0733   0.7640   0.0136
  -2.500   0.0742   0.00954   0.00255  -0.0730   0.7555   0.0148
  -2.000   0.1277   0.00917   0.00201  -0.0724   0.7388   0.0161
  -1.750   0.1546   0.00904   0.00179  -0.0721   0.7311   0.0174
  -1.500   0.1815   0.00888   0.00160  -0.0718   0.7230   0.0241
  -1.250   0.2072   0.00848   0.00147  -0.0715   0.7155   0.1067
  -1.000   0.2325   0.00806   0.00138  -0.0712   0.7077   0.2197
  -0.750   0.2570   0.00753   0.00134  -0.0709   0.7003   0.3833
  -0.500   0.2799   0.00696   0.00135  -0.0701   0.6926   0.5733
  -0.250   0.3042   0.00668   0.00136  -0.0693   0.6848   0.6716
   0.250   0.3582   0.00611   0.00146  -0.0682   0.6682   0.9276
   0.500   0.4081   0.00615   0.00145  -0.0729   0.6585   0.9786
   1.000   0.4828   0.00627   0.00142  -0.0771   0.6389   0.9985
   1.250   0.5107   0.00633   0.00143  -0.0772   0.6290   1.0000
   1.500   0.5353   0.00642   0.00146  -0.0765   0.6182   1.0000
   1.750   0.5598   0.00651   0.00149  -0.0757   0.6061   1.0000
   2.000   0.5844   0.00660   0.00154  -0.0750   0.5930   1.0000
   2.250   0.6090   0.00671   0.00159  -0.0743   0.5791   1.0000
   2.500   0.6334   0.00682   0.00165  -0.0736   0.5644   1.0000
   2.750   0.6578   0.00695   0.00173  -0.0729   0.5473   1.0000
   3.000   0.6817   0.00711   0.00181  -0.0720   0.5262   1.0000
   3.250   0.7051   0.00731   0.00191  -0.0711   0.5002   1.0000
   3.500   0.7281   0.00755   0.00204  -0.0702   0.4709   1.0000
   3.750   0.7507   0.00785   0.00221  -0.0692   0.4387   1.0000
   4.000   0.7733   0.00816   0.00239  -0.0682   0.4045   1.0000
   4.250   0.7954   0.00853   0.00260  -0.0672   0.3679   1.0000
   4.500   0.8173   0.00894   0.00284  -0.0662   0.3291   1.0000
   4.750   0.8387   0.00941   0.00311  -0.0651   0.2871   1.0000
   5.000   0.8599   0.00990   0.00343  -0.0641   0.2454   1.0000
   5.250   0.8819   0.01034   0.00373  -0.0631   0.2130   1.0000
   5.500   0.9043   0.01075   0.00403  -0.0623   0.1864   1.0000
   5.750   0.9264   0.01117   0.00435  -0.0614   0.1619   1.0000
   6.000   0.9484   0.01162   0.00469  -0.0605   0.1371   1.0000
   6.250   0.9701   0.01208   0.00506  -0.0595   0.1145   1.0000
   6.500   0.9920   0.01252   0.00545  -0.0586   0.0973   1.0000
   6.750   1.0139   0.01295   0.00584  -0.0577   0.0837   1.0000
   7.000   1.0360   0.01337   0.00623  -0.0568   0.0727   1.0000
   7.250   1.0577   0.01380   0.00664  -0.0559   0.0623   1.0000
   7.500   1.0790   0.01426   0.00708  -0.0549   0.0531   1.0000
   7.750   1.0998   0.01475   0.00756  -0.0539   0.0448   1.0000
   8.000   1.1207   0.01521   0.00802  -0.0529   0.0388   1.0000
   8.250   1.1414   0.01568   0.00851  -0.0518   0.0343   1.0000
   8.500   1.1622   0.01612   0.00899  -0.0508   0.0310   1.0000
   8.750   1.1816   0.01666   0.00954  -0.0496   0.0272   1.0000
   9.000   1.2014   0.01714   0.01008  -0.0484   0.0247   1.0000
   9.250   1.2206   0.01764   0.01063  -0.0472   0.0214   1.0000
   9.500   1.2377   0.01828   0.01129  -0.0457   0.0176   1.0000
   9.750   1.2550   0.01886   0.01192  -0.0442   0.0149   1.0000
  10.000   1.2689   0.01959   0.01265  -0.0422   0.0120   1.0000
  10.250   1.2827   0.02023   0.01338  -0.0401   0.0107   1.0000
  10.500   1.2949   0.02097   0.01417  -0.0378   0.0095   1.0000
  10.750   1.3060   0.02181   0.01507  -0.0355   0.0087   1.0000
  11.000   1.3149   0.02281   0.01617  -0.0330   0.0079   1.0000
  11.250   1.3258   0.02368   0.01713  -0.0309   0.0075   1.0000
  11.500   1.3361   0.02460   0.01816  -0.0289   0.0071   1.0000
  11.750   1.3453   0.02564   0.01932  -0.0269   0.0066   1.0000
  12.000   1.3543   0.02671   0.02048  -0.0250   0.0062   1.0000
  12.250   1.3606   0.02804   0.02191  -0.0231   0.0058   1.0000
  12.500   1.3651   0.02957   0.02355  -0.0212   0.0056   1.0000
  12.750   1.3657   0.03150   0.02561  -0.0192   0.0052   1.0000
  13.000   1.3654   0.03361   0.02786  -0.0175   0.0051   1.0000
  13.250   1.3707   0.03532   0.02969  -0.0164   0.0049   1.0000
  13.500   1.3733   0.03735   0.03185  -0.0153   0.0048   1.0000
  13.750   1.3745   0.03961   0.03426  -0.0144   0.0047   1.0000
  14.000   1.3736   0.04221   0.03699  -0.0138   0.0046   1.0000
  14.250   1.3724   0.04492   0.03985  -0.0134   0.0045   1.0000
  14.500   1.3712   0.04778   0.04285  -0.0132   0.0043   1.0000
  14.750   1.3682   0.05096   0.04617  -0.0133   0.0041   1.0000
  15.000   1.3630   0.05456   0.04991  -0.0137   0.0040   1.0000
  15.250   1.3596   0.05810   0.05360  -0.0144   0.0039   1.0000
  15.500   1.3538   0.06214   0.05778  -0.0155   0.0038   1.0000
  15.750   1.3449   0.06685   0.06265  -0.0170   0.0037   1.0000
  16.000   1.3324   0.07242   0.06838  -0.0192   0.0037   1.0000
  16.250   1.3233   0.07773   0.07383  -0.0215   0.0036   1.0000
  16.500   1.3083   0.08435   0.08062  -0.0246   0.0036   1.0000
  16.750   1.2972   0.09061   0.08701  -0.0278   0.0035   1.0000
  17.000   1.2805   0.09815   0.09472  -0.0317   0.0036   1.0000
  17.250   1.2626   0.10626   0.10298  -0.0361   0.0036   1.0000
  17.500   1.2435   0.11494   0.11182  -0.0409   0.0036   1.0000
  17.750   1.2240   0.12391   0.12094  -0.0459   0.0036   1.0000
  18.000   1.2069   0.13263   0.12978  -0.0509   0.0036   1.0000
  18.250   1.1847   0.14277   0.14007  -0.0567   0.0037   1.0000
  18.500   1.1667   0.15215   0.14956  -0.0622   0.0037   1.0000
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