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S4320 (s4320-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S4320 (s4320-il)
Reynolds number: 50,000
Max Cl/Cd: 40.03 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4320-il-50000-n5.txt
Download as CSV file: xf-s4320-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4320                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2885   0.10423   0.09783  -0.0333   1.0000   0.1066
  -8.000  -0.3018   0.10355   0.09734  -0.0350   1.0000   0.1077
  -7.750  -0.3157   0.10267   0.09665  -0.0355   1.0000   0.1080
  -7.500  -0.2948   0.09690   0.09090  -0.0329   1.0000   0.1100
  -7.250  -0.2946   0.09449   0.08859  -0.0311   1.0000   0.1116
  -7.000  -0.3032   0.09300   0.08725  -0.0287   1.0000   0.1131
  -6.750  -0.3156   0.09187   0.08625  -0.0262   1.0000   0.1145
  -6.500  -0.3296   0.09081   0.08532  -0.0240   1.0000   0.1163
  -6.250  -0.3200   0.08783   0.08232  -0.0393   0.9862   0.1226
  -6.000  -0.2856   0.07677   0.07102  -0.0507   0.9762   0.0658
  -5.750  -0.2627   0.07259   0.06683  -0.0526   0.9687   0.0643
  -5.500  -0.2376   0.06787   0.06204  -0.0578   0.9591   0.0618
  -5.000  -0.1667   0.05372   0.04713  -0.0780   0.9405   0.0522
  -4.750  -0.1371   0.04936   0.04247  -0.0824   0.9315   0.0515
  -4.500  -0.1022   0.04470   0.03735  -0.0876   0.9239   0.0513
  -4.250  -0.0648   0.04053   0.03242  -0.0922   0.9161   0.0528
  -4.000  -0.0345   0.03770   0.02942  -0.0945   0.9084   0.0551
  -3.750   0.0005   0.03483   0.02603  -0.0969   0.9011   0.0558
  -3.500   0.0332   0.03251   0.02323  -0.0984   0.8933   0.0569
  -3.250   0.0677   0.03052   0.02076  -0.0998   0.8861   0.0588
  -3.000   0.0987   0.02912   0.01894  -0.1003   0.8779   0.0634
  -2.750   0.1320   0.02772   0.01723  -0.1011   0.8709   0.0679
  -2.500   0.1601   0.02673   0.01608  -0.1009   0.8624   0.0721
  -2.250   0.1926   0.02576   0.01480  -0.1012   0.8556   0.0785
  -2.000   0.2199   0.02511   0.01407  -0.1010   0.8465   0.0914
  -1.750   0.2536   0.02420   0.01316  -0.1018   0.8400   0.1205
  -1.500   0.2800   0.02317   0.01277  -0.1021   0.8307   0.2349
  -1.250   0.3053   0.02159   0.01261  -0.1013   0.8247   0.5618
  -1.000   0.3302   0.02073   0.01234  -0.0991   0.8151   1.0000
  -0.750   0.3610   0.02089   0.01204  -0.0994   0.8074   1.0000
  -0.500   0.3887   0.02114   0.01192  -0.0994   0.7983   1.0000
  -0.250   0.4158   0.02140   0.01187  -0.0992   0.7892   1.0000
   0.000   0.4459   0.02156   0.01174  -0.0993   0.7816   1.0000
   0.250   0.4708   0.02189   0.01186  -0.0988   0.7715   1.0000
   0.500   0.5002   0.02206   0.01179  -0.0988   0.7638   1.0000
   0.750   0.5260   0.02236   0.01191  -0.0984   0.7541   1.0000
   1.000   0.5518   0.02266   0.01207  -0.0979   0.7444   1.0000
   1.250   0.5814   0.02278   0.01202  -0.0977   0.7368   1.0000
   1.500   0.6053   0.02316   0.01230  -0.0971   0.7259   1.0000
   1.750   0.6314   0.02342   0.01247  -0.0966   0.7163   1.0000
   2.000   0.6601   0.02354   0.01249  -0.0963   0.7079   1.0000
   2.250   0.6840   0.02391   0.01280  -0.0956   0.6966   1.0000
   2.500   0.7096   0.02418   0.01301  -0.0950   0.6862   1.0000
   2.750   0.7387   0.02421   0.01297  -0.0945   0.6777   1.0000
   3.000   0.7622   0.02458   0.01335  -0.0938   0.6657   1.0000
   3.250   0.7866   0.02489   0.01365  -0.0930   0.6542   1.0000
   3.500   0.8123   0.02510   0.01385  -0.0923   0.6433   1.0000
   3.750   0.8409   0.02511   0.01382  -0.0918   0.6337   1.0000
   4.000   0.8644   0.02544   0.01422  -0.0909   0.6209   1.0000
   4.250   0.8883   0.02574   0.01456  -0.0901   0.6082   1.0000
   4.500   0.9126   0.02600   0.01486  -0.0892   0.5954   1.0000
   4.750   0.9371   0.02623   0.01513  -0.0884   0.5825   1.0000
   5.000   0.9616   0.02644   0.01543  -0.0875   0.5692   1.0000
   5.250   0.9860   0.02665   0.01569  -0.0865   0.5554   1.0000
   5.500   1.0100   0.02688   0.01597  -0.0856   0.5411   1.0000
   5.750   1.0335   0.02712   0.01628  -0.0846   0.5260   1.0000
   6.000   1.0567   0.02740   0.01667  -0.0835   0.5105   1.0000
   6.250   1.0797   0.02768   0.01702  -0.0825   0.4945   1.0000
   6.500   1.1026   0.02797   0.01737  -0.0814   0.4782   1.0000
   6.750   1.1254   0.02828   0.01772  -0.0803   0.4616   1.0000
   7.000   1.1474   0.02866   0.01818  -0.0791   0.4445   1.0000
   7.250   1.1668   0.02925   0.01888  -0.0779   0.4261   1.0000
   7.500   1.1866   0.02982   0.01951  -0.0766   0.4080   1.0000
   7.750   1.2065   0.03040   0.02013  -0.0753   0.3902   1.0000
   8.000   1.2260   0.03103   0.02081  -0.0740   0.3729   1.0000
   8.250   1.2423   0.03192   0.02180  -0.0726   0.3548   1.0000
   8.500   1.2584   0.03282   0.02277  -0.0711   0.3373   1.0000
   8.750   1.2741   0.03377   0.02378  -0.0696   0.3206   1.0000
   9.000   1.2888   0.03479   0.02485  -0.0681   0.3046   1.0000
   9.250   1.3026   0.03589   0.02605  -0.0666   0.2893   1.0000
   9.500   1.3150   0.03708   0.02731  -0.0649   0.2745   1.0000
   9.750   1.3263   0.03837   0.02869  -0.0633   0.2605   1.0000
  10.000   1.3350   0.03974   0.03018  -0.0614   0.2474   1.0000
  10.250   1.3424   0.04122   0.03177  -0.0595   0.2350   1.0000
  10.500   1.3500   0.04280   0.03346  -0.0577   0.2235   1.0000
  10.750   1.3573   0.04441   0.03515  -0.0561   0.2126   1.0000
  11.000   1.3652   0.04601   0.03685  -0.0546   0.2022   1.0000
  11.250   1.3677   0.04817   0.03924  -0.0531   0.1922   1.0000
  11.500   1.3718   0.05025   0.04146  -0.0518   0.1830   1.0000
  11.750   1.3790   0.05204   0.04327  -0.0506   0.1741   1.0000
  12.000   1.3770   0.05489   0.04642  -0.0495   0.1659   1.0000
  12.250   1.3807   0.05718   0.04881  -0.0486   0.1582   1.0000
  12.500   1.3784   0.06015   0.05200  -0.0479   0.1508   1.0000
  12.750   1.3783   0.06302   0.05501  -0.0474   0.1439   1.0000
  13.000   1.3744   0.06641   0.05862  -0.0471   0.1375   1.0000
  13.250   1.3725   0.06960   0.06193  -0.0469   0.1312   1.0000
  13.500   1.3615   0.07412   0.06672  -0.0475   0.1258   1.0000
  13.750   1.3627   0.07694   0.06961  -0.0474   0.1196   1.0000
  14.000   1.3439   0.08309   0.07610  -0.0491   0.1158   1.0000
  14.250   1.3326   0.08812   0.08131  -0.0505   0.1112   1.0000
  14.500   1.3268   0.09230   0.08557  -0.0516   0.1060   1.0000
  14.750   1.3007   0.10070   0.09427  -0.0553   0.1041   1.0000
  15.000   1.2692   0.11092   0.10472  -0.0604   0.1031   1.0000
  15.250   1.2225   0.12586   0.11974  -0.0689   0.1041   1.0000
  15.500   1.1569   0.14843   0.14216  -0.0825   0.1050   1.0000
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