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S4320 (s4320-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S4320 (s4320-il)
Reynolds number: 50,000
Max Cl/Cd: 32.32 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4320-il-50000.txt
Download as CSV file: xf-s4320-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3072   0.11196   0.10562  -0.0302   1.0000   0.1668
  -8.250  -0.2788   0.10488   0.09852  -0.0280   1.0000   0.1746
  -8.000  -0.2887   0.10435   0.09814  -0.0291   1.0000   0.1807
  -7.750  -0.2793   0.10030   0.09417  -0.0284   1.0000   0.1857
  -7.500  -0.2804   0.09845   0.09244  -0.0276   1.0000   0.1937
  -7.250  -0.3060   0.09934   0.09358  -0.0262   1.0000   0.1961
  -7.000  -0.2883   0.09456   0.08883  -0.0241   1.0000   0.2062
  -6.750  -0.3125   0.09489   0.08936  -0.0207   1.0000   0.2093
  -6.500  -0.3419   0.09568   0.09034  -0.0184   1.0000   0.2110
  -6.250  -0.3343   0.09204   0.08675  -0.0143   1.0000   0.2196
  -6.000  -0.3562   0.09200   0.08685  -0.0125   1.0000   0.2246
  -5.750  -0.3760   0.09142   0.08641  -0.0129   1.0000   0.2274
  -5.500  -0.3746   0.08887   0.08390  -0.0088   1.0000   0.2392
  -5.250  -0.3792   0.08661   0.08171  -0.0068   1.0000   0.2464
  -5.000  -0.3915   0.08586   0.08105  -0.0101   1.0000   0.2571
  -4.750  -0.3896   0.08316   0.07838  -0.0059   1.0000   0.2697
  -4.500  -0.3893   0.08058   0.07586  -0.0035   1.0000   0.2809
  -4.250  -0.3895   0.07826   0.07359  -0.0027   1.0000   0.2948
  -4.000  -0.3882   0.07605   0.07142  -0.0023   1.0000   0.3122
  -3.750  -0.3857   0.07374   0.06913  -0.0030   1.0000   0.3334
  -3.500  -0.3826   0.07126   0.06672   0.0002   1.0000   0.3525
  -3.250  -0.3791   0.06901   0.06450   0.0016   1.0000   0.3801
  -3.000  -0.3764   0.06678   0.06233   0.0046   1.0000   0.4104
  -2.750  -0.3752   0.06471   0.06031   0.0089   1.0000   0.4458
  -2.250  -0.1237   0.04244   0.03508  -0.0623   0.9946   0.1485
  -2.000  -0.0671   0.03873   0.03044  -0.0686   0.9872   0.1343
  -1.750  -0.0182   0.03650   0.02758  -0.0730   0.9794   0.1329
  -1.500   0.0307   0.03502   0.02543  -0.0771   0.9711   0.1384
  -1.250   0.0681   0.03389   0.02410  -0.0792   0.9622   0.1440
  -1.000   0.1105   0.03304   0.02292  -0.0817   0.9536   0.1558
  -0.750   0.1513   0.03245   0.02229  -0.0840   0.9443   0.1899
  -0.500   0.1909   0.02908   0.02148  -0.0852   0.9379   0.6279
  -0.250   0.2287   0.02912   0.02108  -0.0863   0.9272   1.0000
   0.000   0.2592   0.02993   0.02142  -0.0877   0.9156   1.0000
   0.250   0.2901   0.03080   0.02191  -0.0891   0.9042   1.0000
   0.500   0.3234   0.03171   0.02251  -0.0909   0.8928   1.0000
   0.750   0.3600   0.03265   0.02315  -0.0931   0.8813   1.0000
   1.000   0.3958   0.03354   0.02381  -0.0950   0.8695   1.0000
   1.250   0.4215   0.03444   0.02452  -0.0955   0.8568   1.0000
   1.500   0.4490   0.03537   0.02530  -0.0962   0.8441   1.0000
   1.750   0.4779   0.03630   0.02610  -0.0970   0.8312   1.0000
   2.000   0.5076   0.03723   0.02692  -0.0979   0.8182   1.0000
   2.250   0.5386   0.03812   0.02772  -0.0988   0.8050   1.0000
   2.500   0.5703   0.03898   0.02851  -0.0997   0.7918   1.0000
   2.750   0.6031   0.03978   0.02926  -0.1006   0.7784   1.0000
   3.000   0.6371   0.04049   0.02993  -0.1015   0.7648   1.0000
   3.250   0.6693   0.04117   0.03060  -0.1020   0.7510   1.0000
   3.500   0.6969   0.04195   0.03138  -0.1020   0.7366   1.0000
   3.750   0.7250   0.04269   0.03215  -0.1019   0.7221   1.0000
   4.000   0.7538   0.04336   0.03284  -0.1018   0.7075   1.0000
   4.250   0.7838   0.04390   0.03343  -0.1016   0.6928   1.0000
   4.500   0.8128   0.04440   0.03397  -0.1012   0.6781   1.0000
   4.750   0.8423   0.04475   0.03442  -0.1005   0.6634   1.0000
   5.000   0.8723   0.04496   0.03470  -0.0998   0.6486   1.0000
   5.250   0.9026   0.04503   0.03485  -0.0988   0.6339   1.0000
   5.500   0.9335   0.04494   0.03489  -0.0977   0.6192   1.0000
   6.000   0.9627   0.04729   0.03741  -0.0945   0.5841   1.0000
   6.250   0.9920   0.04715   0.03738  -0.0931   0.5686   1.0000
   6.500   1.0231   0.04676   0.03717  -0.0917   0.5533   1.0000
   6.750   1.0571   0.04598   0.03652  -0.0902   0.5380   1.0000
   7.000   1.0922   0.04503   0.03571  -0.0887   0.5224   1.0000
   7.250   1.1319   0.04357   0.03441  -0.0872   0.5064   1.0000
   7.500   1.1760   0.04166   0.03260  -0.0859   0.4899   1.0000
   7.750   1.1993   0.04186   0.03292  -0.0842   0.4713   1.0000
   8.000   1.2226   0.04207   0.03324  -0.0825   0.4520   1.0000
   8.250   1.2617   0.04085   0.03208  -0.0813   0.4327   1.0000
   8.500   1.2840   0.04132   0.03264  -0.0797   0.4130   1.0000
   8.750   1.3046   0.04205   0.03348  -0.0781   0.3934   1.0000
   9.000   1.3412   0.04150   0.03285  -0.0771   0.3728   1.0000
   9.250   1.3516   0.04330   0.03486  -0.0752   0.3548   1.0000
   9.500   1.3683   0.04460   0.03627  -0.0735   0.3364   1.0000
   9.750   1.3921   0.04550   0.03719  -0.0722   0.3181   1.0000
  10.000   1.4151   0.04665   0.03833  -0.0711   0.3004   1.0000
  10.250   1.4268   0.04873   0.04058  -0.0693   0.2854   1.0000
  10.500   1.4383   0.05080   0.04285  -0.0676   0.2709   1.0000
  10.750   1.4509   0.05290   0.04508  -0.0659   0.2570   1.0000
  11.000   1.4653   0.05504   0.04733  -0.0645   0.2437   1.0000
  11.250   1.4382   0.05970   0.05248  -0.0610   0.2387   1.0000
  11.500   1.0834   0.11138   0.10364  -0.0792   0.2848   1.0000
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