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S4053 (s4053-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S4053 (s4053-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.64 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4053-il-1000000-n5.txt
Download as CSV file: xf-s4053-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4065   0.08776   0.08614  -0.0315   1.0000   0.0058
  -8.750  -0.4103   0.08382   0.08222  -0.0326   1.0000   0.0057
  -8.500  -0.4152   0.08013   0.07856  -0.0334   1.0000   0.0055
  -8.000  -0.4089   0.06789   0.06635  -0.0471   0.9884   0.0054
  -7.750  -0.3975   0.05851   0.05692  -0.0605   0.9785   0.0054
  -7.500  -0.3808   0.04766   0.04589  -0.0731   0.9667   0.0056
  -7.250  -0.3664   0.03562   0.03341  -0.0813   0.9461   0.0059
  -7.000  -0.3586   0.02548   0.02255  -0.0828   0.9170   0.0063
  -6.750  -0.3454   0.02137   0.01790  -0.0816   0.8914   0.0065
  -6.500  -0.3283   0.01878   0.01486  -0.0803   0.8711   0.0066
  -6.250  -0.3082   0.01696   0.01269  -0.0792   0.8540   0.0067
  -6.000  -0.2859   0.01570   0.01115  -0.0784   0.8389   0.0068
  -5.750  -0.2622   0.01479   0.01001  -0.0777   0.8250   0.0070
  -5.500  -0.2380   0.01395   0.00897  -0.0771   0.8125   0.0071
  -5.250  -0.2139   0.01298   0.00778  -0.0764   0.8007   0.0072
  -4.750  -0.1641   0.01146   0.00594  -0.0753   0.7792   0.0073
  -4.500  -0.1387   0.01088   0.00524  -0.0748   0.7695   0.0074
  -4.250  -0.1128   0.01048   0.00473  -0.0744   0.7602   0.0075
  -4.000  -0.0883   0.00966   0.00378  -0.0738   0.7509   0.0079
  -3.750  -0.0628   0.00916   0.00318  -0.0733   0.7427   0.0085
  -3.500  -0.0363   0.00891   0.00287  -0.0730   0.7341   0.0089
  -3.250  -0.0095   0.00868   0.00260  -0.0728   0.7263   0.0094
  -3.000   0.0172   0.00849   0.00234  -0.0725   0.7185   0.0098
  -2.750   0.0442   0.00829   0.00208  -0.0723   0.7108   0.0102
  -2.500   0.0711   0.00813   0.00186  -0.0721   0.7035   0.0106
  -2.250   0.0984   0.00799   0.00168  -0.0719   0.6961   0.0111
  -2.000   0.1255   0.00788   0.00152  -0.0717   0.6890   0.0116
  -1.750   0.1529   0.00776   0.00136  -0.0716   0.6816   0.0118
  -1.500   0.1801   0.00765   0.00119  -0.0714   0.6747   0.0127
  -1.250   0.2075   0.00755   0.00107  -0.0712   0.6671   0.0160
  -1.000   0.2342   0.00732   0.00097  -0.0710   0.6599   0.0633
  -0.750   0.2606   0.00707   0.00090  -0.0708   0.6517   0.1324
  -0.500   0.2870   0.00682   0.00085  -0.0706   0.6433   0.2120
  -0.250   0.3125   0.00649   0.00084  -0.0703   0.6343   0.3323
   0.000   0.3376   0.00607   0.00084  -0.0700   0.6252   0.4833
   0.250   0.3637   0.00589   0.00085  -0.0697   0.6166   0.5624
   0.500   0.3883   0.00562   0.00088  -0.0691   0.6073   0.6795
   0.750   0.4123   0.00538   0.00092  -0.0682   0.5975   0.7792
   1.000   0.4335   0.00509   0.00099  -0.0665   0.5869   0.9057
   1.250   0.4738   0.00513   0.00105  -0.0691   0.5725   0.9687
   1.500   0.5075   0.00523   0.00108  -0.0704   0.5568   0.9825
   2.000   0.5759   0.00547   0.00116  -0.0733   0.5217   0.9947
   2.250   0.6107   0.00562   0.00121  -0.0750   0.4990   0.9991
   2.500   0.6370   0.00581   0.00129  -0.0748   0.4718   1.0000
   2.750   0.6601   0.00605   0.00140  -0.0738   0.4414   1.0000
   3.000   0.6831   0.00630   0.00151  -0.0729   0.4098   1.0000
   3.250   0.7059   0.00658   0.00165  -0.0719   0.3762   1.0000
   3.500   0.7286   0.00687   0.00180  -0.0710   0.3435   1.0000
   3.750   0.7512   0.00719   0.00198  -0.0700   0.3098   1.0000
   4.000   0.7740   0.00750   0.00216  -0.0691   0.2795   1.0000
   4.250   0.7957   0.00791   0.00238  -0.0680   0.2384   1.0000
   4.500   0.8180   0.00830   0.00260  -0.0671   0.2041   1.0000
   4.750   0.8415   0.00859   0.00280  -0.0663   0.1822   1.0000
   5.000   0.8649   0.00890   0.00303  -0.0656   0.1615   1.0000
   5.250   0.8881   0.00923   0.00326  -0.0648   0.1394   1.0000
   5.500   0.9111   0.00959   0.00352  -0.0640   0.1178   1.0000
   5.750   0.9344   0.00991   0.00377  -0.0633   0.1010   1.0000
   6.000   0.9579   0.01023   0.00403  -0.0626   0.0878   1.0000
   6.250   0.9814   0.01054   0.00430  -0.0619   0.0767   1.0000
   6.500   1.0047   0.01086   0.00460  -0.0612   0.0663   1.0000
   6.750   1.0274   0.01124   0.00492  -0.0604   0.0541   1.0000
   7.000   1.0499   0.01162   0.00525  -0.0595   0.0440   1.0000
   7.250   1.0728   0.01197   0.00557  -0.0588   0.0379   1.0000
   7.500   1.0960   0.01229   0.00589  -0.0581   0.0339   1.0000
   7.750   1.1189   0.01262   0.00624  -0.0573   0.0304   1.0000
   8.000   1.1412   0.01299   0.00661  -0.0565   0.0266   1.0000
   8.250   1.1640   0.01331   0.00696  -0.0558   0.0248   1.0000
   8.500   1.1860   0.01369   0.00734  -0.0549   0.0215   1.0000
   8.750   1.2070   0.01413   0.00777  -0.0539   0.0177   1.0000
   9.000   1.2278   0.01456   0.00821  -0.0529   0.0145   1.0000
   9.250   1.2476   0.01507   0.00872  -0.0517   0.0111   1.0000
   9.500   1.2666   0.01561   0.00927  -0.0504   0.0088   1.0000
   9.750   1.2860   0.01611   0.00980  -0.0492   0.0076   1.0000
  10.000   1.3048   0.01661   0.01035  -0.0479   0.0069   1.0000
  10.250   1.3223   0.01719   0.01096  -0.0464   0.0062   1.0000
  10.500   1.3382   0.01782   0.01164  -0.0446   0.0054   1.0000
  10.750   1.3526   0.01841   0.01229  -0.0426   0.0050   1.0000
  11.000   1.3671   0.01893   0.01288  -0.0406   0.0048   1.0000
  11.250   1.3801   0.01955   0.01358  -0.0384   0.0046   1.0000
  11.500   1.3933   0.02016   0.01425  -0.0364   0.0043   1.0000
  11.750   1.4058   0.02084   0.01499  -0.0343   0.0040   1.0000
  12.000   1.4172   0.02160   0.01582  -0.0322   0.0038   1.0000
  12.250   1.4271   0.02247   0.01676  -0.0300   0.0036   1.0000
  12.500   1.4361   0.02343   0.01779  -0.0279   0.0033   1.0000
  12.750   1.4423   0.02463   0.01909  -0.0256   0.0031   1.0000
  13.000   1.4491   0.02583   0.02038  -0.0236   0.0030   1.0000
  13.250   1.4581   0.02690   0.02153  -0.0219   0.0029   1.0000
  13.500   1.4656   0.02813   0.02285  -0.0203   0.0029   1.0000
  13.750   1.4727   0.02945   0.02426  -0.0189   0.0027   1.0000
  14.000   1.4768   0.03109   0.02603  -0.0173   0.0027   1.0000
  14.250   1.4823   0.03267   0.02770  -0.0161   0.0026   1.0000
  14.500   1.4866   0.03443   0.02956  -0.0150   0.0025   1.0000
  14.750   1.4887   0.03648   0.03172  -0.0141   0.0024   1.0000
  15.000   1.4911   0.03858   0.03392  -0.0133   0.0023   1.0000
  15.250   1.4924   0.04089   0.03634  -0.0127   0.0023   1.0000
  15.500   1.4924   0.04342   0.03897  -0.0123   0.0022   1.0000
  15.750   1.4899   0.04635   0.04202  -0.0122   0.0021   1.0000
  16.000   1.4858   0.04960   0.04539  -0.0123   0.0021   1.0000
  16.250   1.4831   0.05280   0.04870  -0.0127   0.0020   1.0000
  16.500   1.4763   0.05673   0.05276  -0.0134   0.0020   1.0000
  16.750   1.4713   0.06059   0.05671  -0.0144   0.0019   1.0000
  17.000   1.4602   0.06554   0.06182  -0.0160   0.0019   1.0000
  17.250   1.4502   0.07061   0.06701  -0.0179   0.0019   1.0000
  17.500   1.4368   0.07652   0.07305  -0.0204   0.0019   1.0000
  17.750   1.4217   0.08301   0.07969  -0.0235   0.0018   1.0000
  18.000   1.4064   0.08985   0.08667  -0.0269   0.0018   1.0000
  18.250   1.3823   0.09871   0.09571  -0.0316   0.0019   1.0000
  18.500   1.3615   0.10728   0.10442  -0.0362   0.0018   1.0000
  18.750   1.3345   0.11748   0.11479  -0.0420   0.0018   1.0000
  19.000   1.3084   0.12778   0.12524  -0.0479   0.0019   1.0000
  19.250   1.2806   0.13879   0.13640  -0.0543   0.0019   1.0000
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