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S4233-136-84 (s4233-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S4233-136-84 (s4233-il)
Reynolds number: 50,000
Max Cl/Cd: 26.14 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4233-il-50000-n5.txt
Download as CSV file: xf-s4233-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4233-136-84                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3451   0.10395   0.09703  -0.0501   1.0000   0.0484
 -10.250  -0.3468   0.09982   0.09299  -0.0517   1.0000   0.0477
 -10.000  -0.3507   0.09558   0.08885  -0.0533   1.0000   0.0470
  -9.750  -0.3572   0.09125   0.08463  -0.0549   1.0000   0.0463
  -9.500  -0.3682   0.08669   0.08022  -0.0565   1.0000   0.0456
  -9.250  -0.3880   0.08146   0.07513  -0.0582   1.0000   0.0447
  -9.000  -0.4231   0.07628   0.07007  -0.0595   1.0000   0.0434
  -8.750  -0.4732   0.07320   0.06707  -0.0577   1.0000   0.0426
  -8.500  -0.5203   0.06941   0.06307  -0.0571   0.9965   0.0416
  -8.250  -0.5149   0.06417   0.05756  -0.0619   0.9853   0.0414
  -8.000  -0.5082   0.05934   0.05239  -0.0654   0.9748   0.0413
  -7.750  -0.4983   0.05495   0.04756  -0.0680   0.9649   0.0413
  -7.500  -0.4833   0.05086   0.04297  -0.0704   0.9565   0.0416
  -7.250  -0.4646   0.04795   0.03987  -0.0718   0.9483   0.0430
  -7.000  -0.4422   0.04534   0.03698  -0.0733   0.9410   0.0444
  -6.750  -0.4197   0.04275   0.03397  -0.0743   0.9334   0.0460
  -6.500  -0.3937   0.04017   0.03094  -0.0754   0.9269   0.0473
  -6.250  -0.3686   0.03796   0.02831  -0.0757   0.9195   0.0484
  -6.000  -0.3336   0.03583   0.02575  -0.0773   0.9150   0.0500
  -5.750  -0.3113   0.03440   0.02405  -0.0765   0.9068   0.0517
  -5.500  -0.2805   0.03298   0.02258  -0.0775   0.9013   0.0554
  -5.250  -0.2570   0.03200   0.02139  -0.0769   0.8937   0.0611
  -5.000  -0.2304   0.03084   0.02019  -0.0771   0.8873   0.0676
  -4.750  -0.2060   0.02979   0.01901  -0.0767   0.8804   0.0768
  -4.500  -0.1837   0.02869   0.01796  -0.0764   0.8729   0.0974
  -4.250  -0.1580   0.02700   0.01682  -0.0771   0.8674   0.1764
  -4.000  -0.1446   0.02582   0.01654  -0.0759   0.8585   0.3214
  -3.750  -0.1198   0.02529   0.01651  -0.0751   0.8533   0.4525
  -3.500  -0.1057   0.02536   0.01672  -0.0723   0.8443   0.5224
  -3.250  -0.0792   0.02540   0.01671  -0.0712   0.8388   0.5832
  -3.000  -0.0621   0.02558   0.01683  -0.0688   0.8305   0.6259
  -2.750  -0.0375   0.02566   0.01680  -0.0673   0.8245   0.6662
  -2.500  -0.0173   0.02579   0.01683  -0.0653   0.8174   0.7006
  -2.250   0.0040   0.02588   0.01682  -0.0635   0.8104   0.7326
  -2.000   0.0330   0.02584   0.01664  -0.0626   0.8061   0.7640
  -1.750   0.0469   0.02605   0.01676  -0.0600   0.7967   0.7911
  -1.500   0.0760   0.02600   0.01657  -0.0594   0.7919   0.8200
  -1.250   0.0959   0.02618   0.01667  -0.0579   0.7837   0.8474
  -1.000   0.1302   0.02617   0.01652  -0.0586   0.7783   0.8751
  -0.750   0.1709   0.02618   0.01637  -0.0607   0.7734   0.9020
  -0.500   0.2102   0.02636   0.01642  -0.0633   0.7658   0.9289
  -0.250   0.2659   0.02627   0.01615  -0.0686   0.7617   0.9511
   0.000   0.3154   0.02640   0.01613  -0.0735   0.7551   0.9746
   0.250   0.3666   0.02641   0.01600  -0.0787   0.7489   0.9990
   0.500   0.3781   0.02654   0.01601  -0.0767   0.7417   1.0000
   1.000   0.4010   0.02715   0.01639  -0.0727   0.7254   1.0000
   1.250   0.4185   0.02750   0.01662  -0.0715   0.7175   1.0000
   1.500   0.4417   0.02773   0.01675  -0.0710   0.7110   1.0000
   1.750   0.4596   0.02819   0.01713  -0.0700   0.7025   1.0000
   2.000   0.4924   0.02814   0.01699  -0.0705   0.6983   1.0000
   2.500   0.5362   0.02890   0.01765  -0.0693   0.6832   1.0000
   2.750   0.5477   0.02974   0.01847  -0.0676   0.6725   1.0000
   3.000   0.5811   0.02967   0.01836  -0.0681   0.6681   1.0000
   3.250   0.5926   0.03057   0.01926  -0.0664   0.6574   1.0000
   3.500   0.6263   0.03048   0.01916  -0.0669   0.6529   1.0000
   3.750   0.6374   0.03144   0.02014  -0.0653   0.6420   1.0000
   4.000   0.6719   0.03128   0.01999  -0.0657   0.6376   1.0000
   4.250   0.6822   0.03231   0.02106  -0.0640   0.6264   1.0000
   4.500   0.7179   0.03206   0.02086  -0.0645   0.6221   1.0000
   5.000   0.7483   0.03369   0.02259  -0.0620   0.6024   1.0000
   5.250   0.7720   0.03403   0.02302  -0.0614   0.5945   1.0000
   5.500   0.7868   0.03488   0.02394  -0.0601   0.5846   1.0000
   5.750   0.8177   0.03481   0.02395  -0.0601   0.5784   1.0000
   6.000   0.8279   0.03592   0.02514  -0.0584   0.5673   1.0000
   6.250   0.8645   0.03548   0.02484  -0.0587   0.5621   1.0000
   6.500   0.8713   0.03676   0.02621  -0.0568   0.5502   1.0000
   7.000   0.9171   0.03737   0.02708  -0.0552   0.5332   1.0000
   7.250   0.9236   0.03860   0.02842  -0.0531   0.5215   1.0000
   7.500   0.9681   0.03758   0.02757  -0.0539   0.5162   1.0000
   7.750   0.9702   0.03901   0.02911  -0.0514   0.5035   1.0000
   8.000   0.9779   0.04022   0.03046  -0.0495   0.4917   1.0000
   8.250   1.0057   0.04003   0.03043  -0.0488   0.4827   1.0000
   8.500   1.0304   0.03999   0.03056  -0.0479   0.4725   1.0000
   8.750   1.0376   0.04118   0.03189  -0.0460   0.4597   1.0000
   9.000   1.0504   0.04195   0.03283  -0.0445   0.4472   1.0000
   9.250   1.0694   0.04218   0.03322  -0.0431   0.4349   1.0000
   9.500   1.0906   0.04213   0.03333  -0.0418   0.4218   1.0000
   9.750   1.1077   0.04237   0.03371  -0.0403   0.4074   1.0000
  10.000   1.1197   0.04300   0.03448  -0.0386   0.3918   1.0000
  10.250   1.1290   0.04386   0.03550  -0.0369   0.3754   1.0000
  10.500   1.1378   0.04477   0.03652  -0.0352   0.3580   1.0000
  10.750   1.1480   0.04554   0.03737  -0.0335   0.3396   1.0000
  11.000   1.1562   0.04652   0.03840  -0.0319   0.3201   1.0000
  11.250   1.1547   0.04859   0.04057  -0.0305   0.3002   1.0000
  11.500   1.1587   0.05004   0.04201  -0.0290   0.2785   1.0000
  11.750   1.1555   0.05250   0.04451  -0.0280   0.2568   1.0000
  12.000   1.1546   0.05472   0.04669  -0.0269   0.2348   1.0000
  12.250   1.1498   0.05765   0.04963  -0.0262   0.2134   1.0000
  12.500   1.1449   0.06063   0.05252  -0.0257   0.1926   1.0000
  12.750   1.1387   0.06403   0.05587  -0.0254   0.1730   1.0000
  13.000   1.1314   0.06773   0.05950  -0.0254   0.1545   1.0000
  13.250   1.1237   0.07162   0.06328  -0.0257   0.1380   1.0000
  13.500   1.1157   0.07573   0.06729  -0.0262   0.1233   1.0000
  13.750   1.1082   0.07998   0.07147  -0.0269   0.1100   1.0000
  14.000   1.1009   0.08440   0.07586  -0.0278   0.0977   1.0000
  14.250   1.0951   0.08876   0.08024  -0.0288   0.0871   1.0000
  14.500   1.0899   0.09313   0.08464  -0.0299   0.0780   1.0000
  14.750   1.0862   0.09729   0.08875  -0.0309   0.0711   1.0000
  15.000   1.0839   0.10142   0.09300  -0.0319   0.0646   1.0000
  15.250   1.0832   0.10525   0.09686  -0.0328   0.0599   1.0000
  15.500   1.0824   0.10936   0.10115  -0.0339   0.0552   1.0000
  15.750   1.0837   0.11283   0.10458  -0.0348   0.0518   1.0000
  16.000   1.0835   0.11711   0.10909  -0.0361   0.0491   1.0000
  16.250   1.0810   0.12189   0.11411  -0.0379   0.0467   1.0000
  16.500   1.0792   0.12644   0.11880  -0.0398   0.0445   1.0000
  16.750   1.0814   0.13005   0.12244  -0.0411   0.0428   1.0000
  17.000   1.0790   0.13501   0.12754  -0.0433   0.0418   1.0000
  17.250   1.0688   0.14215   0.13496  -0.0471   0.0413   1.0000
  17.500   1.0535   0.15092   0.14399  -0.0521   0.0411   1.0000
  17.750   1.0359   0.16090   0.15416  -0.0581   0.0411   1.0000
  18.000   1.0157   0.17256   0.16593  -0.0651   0.0413   1.0000
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