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S4053 (s4053-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S4053 (s4053-il)
Reynolds number: 50,000
Max Cl/Cd: 39.24 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4053-il-50000-n5.txt
Download as CSV file: xf-s4053-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3085   0.10527   0.09863  -0.0307   1.0000   0.1121
  -9.250  -0.3221   0.10319   0.09666  -0.0330   1.0000   0.1158
  -9.000  -0.3320   0.10052   0.09409  -0.0347   1.0000   0.1164
  -8.750  -0.3315   0.09673   0.09038  -0.0351   1.0000   0.1168
  -8.500  -0.3302   0.09300   0.08667  -0.0352   1.0000   0.1170
  -8.250  -0.3117   0.08797   0.08160  -0.0336   1.0000   0.1081
  -7.750  -0.3974   0.08731   0.08063  -0.0359   1.0000   0.0574
  -7.500  -0.4014   0.08390   0.07734  -0.0365   1.0000   0.0550
  -7.000  -0.4130   0.07415   0.06763  -0.0440   1.0000   0.0479
  -6.750  -0.4116   0.07093   0.06446  -0.0434   1.0000   0.0471
  -6.500  -0.4108   0.06756   0.06110  -0.0433   1.0000   0.0463
  -6.250  -0.4100   0.06405   0.05756  -0.0434   1.0000   0.0458
  -6.000  -0.4082   0.06056   0.05399  -0.0433   1.0000   0.0455
  -5.750  -0.4050   0.05710   0.05040  -0.0431   1.0000   0.0454
  -5.500  -0.3999   0.05364   0.04674  -0.0429   1.0000   0.0457
  -5.250  -0.3924   0.05030   0.04309  -0.0425   1.0000   0.0461
  -5.000  -0.3826   0.04709   0.03956  -0.0420   1.0000   0.0463
  -4.750  -0.3704   0.04400   0.03610  -0.0415   1.0000   0.0465
  -4.500  -0.3561   0.04117   0.03290  -0.0408   1.0000   0.0462
  -4.250  -0.3346   0.03823   0.02952  -0.0411   0.9981   0.0459
  -4.000  -0.2997   0.03511   0.02580  -0.0434   0.9917   0.0459
  -3.750  -0.2645   0.03251   0.02263  -0.0453   0.9852   0.0463
  -3.500  -0.2300   0.03039   0.01998  -0.0467   0.9787   0.0470
  -3.250  -0.1946   0.02864   0.01775  -0.0480   0.9723   0.0481
  -3.000  -0.1618   0.02710   0.01603  -0.0490   0.9656   0.0506
  -2.750  -0.1275   0.02611   0.01488  -0.0505   0.9587   0.0570
  -2.500  -0.0946   0.02511   0.01369  -0.0514   0.9514   0.0645
  -2.250  -0.0590   0.02423   0.01257  -0.0529   0.9448   0.0742
  -2.000  -0.0268   0.02327   0.01162  -0.0539   0.9370   0.1012
  -1.750   0.0020   0.02069   0.01114  -0.0552   0.9316   0.4721
  -1.500   0.0601   0.01940   0.01083  -0.0590   0.9299   1.0000
  -1.250   0.0910   0.01956   0.01055  -0.0599   0.9200   1.0000
  -1.000   0.1256   0.01972   0.01030  -0.0615   0.9119   1.0000
  -0.750   0.1605   0.01988   0.01014  -0.0632   0.9037   1.0000
  -0.500   0.1915   0.02007   0.01006  -0.0641   0.8945   1.0000
  -0.250   0.2305   0.02021   0.00993  -0.0664   0.8880   1.0000
   0.000   0.2585   0.02043   0.00996  -0.0666   0.8779   1.0000
   0.250   0.2905   0.02061   0.00997  -0.0676   0.8695   1.0000
   0.500   0.3235   0.02077   0.00999  -0.0686   0.8613   1.0000
   0.750   0.3509   0.02102   0.01012  -0.0687   0.8513   1.0000
   1.000   0.3842   0.02117   0.01018  -0.0697   0.8434   1.0000
   1.250   0.4132   0.02138   0.01033  -0.0700   0.8338   1.0000
   1.500   0.4402   0.02164   0.01053  -0.0699   0.8235   1.0000
   1.750   0.4719   0.02180   0.01065  -0.0705   0.8149   1.0000
   2.000   0.5011   0.02199   0.01083  -0.0706   0.8050   1.0000
   2.250   0.5268   0.02226   0.01111  -0.0702   0.7939   1.0000
   2.500   0.5545   0.02247   0.01134  -0.0700   0.7832   1.0000
   2.750   0.5854   0.02258   0.01147  -0.0702   0.7733   1.0000
   3.000   0.6137   0.02272   0.01166  -0.0699   0.7620   1.0000
   3.250   0.6392   0.02294   0.01197  -0.0692   0.7494   1.0000
   3.500   0.6650   0.02313   0.01223  -0.0685   0.7365   1.0000
   3.750   0.6911   0.02329   0.01247  -0.0678   0.7232   1.0000
   4.000   0.7173   0.02341   0.01269  -0.0670   0.7093   1.0000
   4.250   0.7435   0.02351   0.01294  -0.0661   0.6947   1.0000
   4.500   0.7699   0.02355   0.01309  -0.0651   0.6791   1.0000
   4.750   0.7969   0.02352   0.01317  -0.0641   0.6628   1.0000
   5.000   0.8177   0.02371   0.01349  -0.0624   0.6428   1.0000
   5.250   0.8425   0.02368   0.01359  -0.0610   0.6229   1.0000
   5.500   0.8641   0.02377   0.01388  -0.0593   0.5999   1.0000
   5.750   0.8861   0.02377   0.01400  -0.0574   0.5744   1.0000
   6.000   0.9065   0.02384   0.01416  -0.0554   0.5448   1.0000
   6.250   0.9267   0.02390   0.01428  -0.0532   0.5108   1.0000
   6.500   0.9449   0.02413   0.01451  -0.0510   0.4715   1.0000
   6.750   0.9617   0.02451   0.01487  -0.0485   0.4271   1.0000
   7.000   0.9759   0.02517   0.01538  -0.0460   0.3788   1.0000
   7.250   0.9875   0.02611   0.01610  -0.0433   0.3296   1.0000
   7.500   0.9973   0.02730   0.01706  -0.0408   0.2844   1.0000
   7.750   1.0057   0.02867   0.01822  -0.0382   0.2440   1.0000
   8.000   1.0141   0.03013   0.01955  -0.0359   0.2091   1.0000
   8.250   1.0226   0.03167   0.02098  -0.0336   0.1817   1.0000
   8.500   1.0308   0.03327   0.02246  -0.0314   0.1607   1.0000
   8.750   1.0399   0.03484   0.02409  -0.0293   0.1412   1.0000
   9.000   1.0512   0.03647   0.02576  -0.0274   0.1269   1.0000
   9.250   1.0663   0.03818   0.02754  -0.0260   0.1150   1.0000
   9.500   1.0799   0.03990   0.02934  -0.0245   0.1036   1.0000
   9.750   1.0938   0.04169   0.03114  -0.0232   0.0942   1.0000
  10.000   1.1133   0.04370   0.03341  -0.0222   0.0857   1.0000
  10.250   1.1268   0.04584   0.03574  -0.0209   0.0778   1.0000
  10.500   1.1385   0.04791   0.03788  -0.0196   0.0713   1.0000
  10.750   1.1507   0.05072   0.04114  -0.0182   0.0658   1.0000
  11.000   1.1541   0.05301   0.04363  -0.0165   0.0608   1.0000
  11.250   1.1592   0.05578   0.04651  -0.0151   0.0567   1.0000
  11.500   1.1572   0.05928   0.05049  -0.0135   0.0542   1.0000
  11.750   1.1513   0.06275   0.05429  -0.0121   0.0518   1.0000
  12.000   1.1447   0.06600   0.05776  -0.0112   0.0495   1.0000
  12.250   1.1420   0.06892   0.06071  -0.0107   0.0471   1.0000
  12.500   1.1319   0.07313   0.06510  -0.0106   0.0459   1.0000
  12.750   1.1137   0.07826   0.07056  -0.0113   0.0455   1.0000
  13.000   1.0948   0.08391   0.07649  -0.0130   0.0453   1.0000
  13.250   1.0738   0.09029   0.08310  -0.0155   0.0453   1.0000
  13.500   1.0531   0.09722   0.09021  -0.0189   0.0455   1.0000
  13.750   1.0317   0.10493   0.09806  -0.0232   0.0458   1.0000
  14.000   1.0111   0.11328   0.10652  -0.0281   0.0462   1.0000
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