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S3025 9.38% (s3025-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S3025 9.38% (s3025-il)
Reynolds number: 50,000
Max Cl/Cd: 33.87 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3025-il-50000.txt
Download as CSV file: xf-s3025-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3025 9.38%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3426   0.10175   0.09524  -0.0253   1.0000   0.2106
  -7.750  -0.3379   0.09838   0.09194  -0.0246   1.0000   0.2168
  -7.500  -0.3465   0.09700   0.09070  -0.0240   1.0000   0.2259
  -7.250  -0.3377   0.09328   0.08705  -0.0227   1.0000   0.2335
  -7.000  -0.3585   0.09294   0.08691  -0.0214   1.0000   0.2412
  -6.750  -0.3465   0.08900   0.08300  -0.0195   1.0000   0.2518
  -6.500  -0.3672   0.08799   0.08222  -0.0187   1.0000   0.2587
  -6.250  -0.3697   0.08590   0.08021  -0.0168   1.0000   0.2708
  -6.000  -0.3643   0.08271   0.07711  -0.0139   1.0000   0.2821
  -5.750  -0.3711   0.08063   0.07515  -0.0118   1.0000   0.2926
  -5.500  -0.3826   0.07893   0.07358  -0.0097   1.0000   0.3051
  -5.000  -0.3983   0.07528   0.07014  -0.0048   1.0000   0.3340
  -4.750  -0.4010   0.07308   0.06802  -0.0013   1.0000   0.3505
  -4.500  -0.4035   0.07099   0.06601   0.0022   1.0000   0.3692
  -3.500  -0.2931   0.04556   0.03853  -0.0413   1.0000   0.1369
  -3.250  -0.2646   0.04146   0.03377  -0.0433   1.0000   0.1227
  -3.000  -0.2407   0.03861   0.03057  -0.0439   1.0000   0.1199
  -2.750  -0.2144   0.03589   0.02729  -0.0445   1.0000   0.1161
  -2.500  -0.1872   0.03352   0.02425  -0.0447   1.0000   0.1130
  -2.250  -0.1627   0.03175   0.02206  -0.0445   1.0000   0.1137
  -2.000  -0.1399   0.03049   0.02055  -0.0440   1.0000   0.1187
  -1.750  -0.1163   0.02933   0.01912  -0.0436   1.0000   0.1287
  -1.500  -0.0937   0.02832   0.01793  -0.0428   1.0000   0.1416
  -1.250  -0.0702   0.02741   0.01709  -0.0423   1.0000   0.1748
  -1.000  -0.0383   0.02521   0.01598  -0.0428   1.0000   0.3632
  -0.750  -0.0194   0.02279   0.01520  -0.0399   1.0000   1.0000
  -0.500   0.0218   0.02379   0.01551  -0.0437   0.9907   1.0000
  -0.250   0.0661   0.02485   0.01603  -0.0479   0.9787   1.0000
   0.000   0.1077   0.02584   0.01660  -0.0517   0.9666   1.0000
   0.250   0.1484   0.02681   0.01723  -0.0553   0.9546   1.0000
   0.500   0.1893   0.02777   0.01788  -0.0588   0.9425   1.0000
   0.750   0.2303   0.02868   0.01855  -0.0622   0.9302   1.0000
   1.000   0.2647   0.02948   0.01917  -0.0644   0.9171   1.0000
   1.250   0.2980   0.03029   0.01981  -0.0663   0.9039   1.0000
   1.500   0.3313   0.03110   0.02049  -0.0682   0.8906   1.0000
   1.750   0.3643   0.03190   0.02120  -0.0699   0.8770   1.0000
   2.000   0.3968   0.03270   0.02192  -0.0715   0.8634   1.0000
   2.250   0.4294   0.03350   0.02266  -0.0729   0.8494   1.0000
   2.500   0.4616   0.03427   0.02340  -0.0742   0.8354   1.0000
   2.750   0.4935   0.03504   0.02416  -0.0754   0.8211   1.0000
   3.000   0.5253   0.03578   0.02489  -0.0764   0.8065   1.0000
   3.250   0.5569   0.03648   0.02562  -0.0772   0.7916   1.0000
   3.500   0.5881   0.03717   0.02634  -0.0779   0.7766   1.0000
   3.750   0.6195   0.03781   0.02706  -0.0785   0.7614   1.0000
   4.000   0.6521   0.03835   0.02767  -0.0791   0.7459   1.0000
   4.250   0.6858   0.03879   0.02820  -0.0796   0.7304   1.0000
   4.500   0.7211   0.03908   0.02863  -0.0800   0.7149   1.0000
   4.750   0.7568   0.03922   0.02889  -0.0802   0.6994   1.0000
   5.000   0.7927   0.03919   0.02899  -0.0801   0.6838   1.0000
   5.250   0.8301   0.03892   0.02887  -0.0799   0.6681   1.0000
   5.500   0.8538   0.03938   0.02950  -0.0785   0.6503   1.0000
   5.750   0.8755   0.03992   0.03018  -0.0769   0.6314   1.0000
   6.000   0.9100   0.03951   0.02994  -0.0760   0.6139   1.0000
   6.250   0.9506   0.03848   0.02913  -0.0750   0.5966   1.0000
   6.500   0.9842   0.03789   0.02870  -0.0736   0.5776   1.0000
   6.750   1.0075   0.03801   0.02899  -0.0717   0.5564   1.0000
   7.000   1.0548   0.03616   0.02731  -0.0708   0.5364   1.0000
   7.250   1.0720   0.03670   0.02802  -0.0685   0.5127   1.0000
   7.500   1.1041   0.03602   0.02745  -0.0668   0.4889   1.0000
   7.750   1.1386   0.03515   0.02664  -0.0653   0.4631   1.0000
   8.000   1.1646   0.03501   0.02656  -0.0634   0.4358   1.0000
   8.250   1.1863   0.03532   0.02693  -0.0613   0.4079   1.0000
   8.500   1.2078   0.03574   0.02736  -0.0592   0.3793   1.0000
   8.750   1.2289   0.03628   0.02790  -0.0571   0.3500   1.0000
   9.000   1.2487   0.03705   0.02857  -0.0551   0.3201   1.0000
   9.250   1.2631   0.03822   0.02973  -0.0526   0.2908   1.0000
   9.500   1.2743   0.03959   0.03109  -0.0499   0.2613   1.0000
   9.750   1.2806   0.04097   0.03244  -0.0467   0.2310   1.0000
  10.000   1.2800   0.04207   0.03343  -0.0430   0.2005   1.0000
  10.250   1.2760   0.04349   0.03470  -0.0392   0.1729   1.0000
  10.500   1.2741   0.04571   0.03682  -0.0358   0.1476   1.0000
  10.750   1.2822   0.04863   0.03943  -0.0336   0.1247   1.0000
  11.000   1.2875   0.05178   0.04269  -0.0314   0.1111   1.0000
  11.250   1.2859   0.05479   0.04604  -0.0286   0.1031   1.0000
  11.500   1.2920   0.05861   0.05005  -0.0269   0.0970   1.0000
  11.750   1.2836   0.06241   0.05427  -0.0243   0.0946   1.0000
  12.000   1.2737   0.06635   0.05854  -0.0221   0.0928   1.0000
  12.250   1.2611   0.07051   0.06299  -0.0205   0.0915   1.0000
  12.500   1.2420   0.07514   0.06791  -0.0196   0.0911   1.0000
  12.750   1.2125   0.08072   0.07380  -0.0199   0.0923   1.0000
  13.000   1.1796   0.08738   0.08071  -0.0219   0.0938   1.0000
  13.250   1.1469   0.09504   0.08856  -0.0252   0.0955   1.0000
  13.500   1.1175   0.10342   0.09705  -0.0295   0.0972   1.0000
  13.750   1.0918   0.11232   0.10601  -0.0341   0.0986   1.0000
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