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NREL's S802 Airfoil (s802-nr) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NREL's S802 Airfoil (s802-nr)
Reynolds number: 100,000
Max Cl/Cd: 61.01 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s802-nr-100000.txt
Download as CSV file: xf-s802-nr-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S802 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4227   0.10658   0.10234  -0.0326   1.0000   0.1026
  -8.000  -0.4524   0.10629   0.10218  -0.0305   1.0000   0.1030
  -7.750  -0.4803   0.10571   0.10170  -0.0284   1.0000   0.1032
  -7.500  -0.4598   0.10015   0.09614  -0.0283   0.9979   0.1057
  -7.250  -0.4330   0.09660   0.09253  -0.0291   0.9947   0.1106
  -7.000  -0.4355   0.09290   0.08887  -0.0365   0.9862   0.1163
  -6.750  -0.4356   0.08598   0.08194  -0.0493   0.9769   0.1200
  -6.500  -0.4109   0.08457   0.08054  -0.0441   0.9747   0.1269
  -6.250  -0.4104   0.07715   0.07298  -0.0592   0.9641   0.1351
  -6.000  -0.3868   0.07529   0.07118  -0.0563   0.9615   0.1427
  -5.750  -0.3837   0.07040   0.06618  -0.0624   0.9538   0.1517
  -5.500  -0.3643   0.06592   0.06151  -0.0691   0.9489   0.1657
  -5.250  -0.3498   0.06370   0.05934  -0.0669   0.9445   0.1711
  -5.000  -0.3344   0.06018   0.05571  -0.0699   0.9390   0.1845
  -4.750  -0.2713   0.04317   0.03687  -0.0884   0.9365   0.0927
  -4.500  -0.2244   0.03747   0.02987  -0.0929   0.9348   0.0766
  -4.250  -0.1965   0.03591   0.02786  -0.0934   0.9313   0.0758
  -4.000  -0.1688   0.03369   0.02532  -0.0940   0.9276   0.0749
  -3.750  -0.1352   0.03187   0.02312  -0.0954   0.9244   0.0749
  -3.500  -0.0989   0.03033   0.02126  -0.0970   0.9218   0.0760
  -3.250  -0.0626   0.02901   0.01998  -0.0990   0.9198   0.0819
  -3.000  -0.0452   0.02858   0.01945  -0.0975   0.9153   0.0863
  -2.750  -0.0183   0.02776   0.01862  -0.0975   0.9115   0.0916
  -2.500   0.0142   0.02703   0.01795  -0.0986   0.9084   0.1049
  -2.250   0.0517   0.02574   0.01719  -0.1009   0.9063   0.1780
  -2.000   0.0715   0.02400   0.01783  -0.0994   0.9039   0.6521
  -1.750   0.0724   0.02472   0.01865  -0.0935   0.8980   0.7612
  -1.500   0.0759   0.02527   0.01924  -0.0872   0.8937   0.8256
  -1.250   0.0860   0.02551   0.01940  -0.0821   0.8903   0.8728
  -1.000   0.0800   0.02566   0.01954  -0.0756   0.8845   0.9050
  -0.750   0.0928   0.02556   0.01939  -0.0721   0.8800   0.9534
  -0.500   0.1442   0.02573   0.01934  -0.0772   0.8767   1.0000
  -0.250   0.1724   0.02618   0.01960  -0.0785   0.8726   1.0000
   0.000   0.1941   0.02666   0.01994  -0.0789   0.8670   1.0000
   0.250   0.2294   0.02708   0.02020  -0.0812   0.8630   1.0000
   0.500   0.2733   0.02748   0.02044  -0.0847   0.8599   1.0000
   0.750   0.2853   0.02815   0.02104  -0.0836   0.8528   1.0000
   1.000   0.3206   0.02859   0.02138  -0.0857   0.8480   1.0000
   1.250   0.3653   0.02896   0.02164  -0.0890   0.8447   1.0000
   1.500   0.3765   0.02974   0.02238  -0.0878   0.8364   1.0000
   1.750   0.4157   0.03011   0.02268  -0.0902   0.8317   1.0000
   2.000   0.4400   0.03077   0.02330  -0.0906   0.8247   1.0000
   2.250   0.4712   0.03124   0.02374  -0.0919   0.8182   1.0000
   2.500   0.5190   0.03137   0.02385  -0.0953   0.8144   1.0000
   2.750   0.5313   0.03223   0.02470  -0.0939   0.8039   1.0000
   3.000   0.5796   0.03221   0.02468  -0.0971   0.7996   1.0000
   3.250   0.5948   0.03301   0.02549  -0.0961   0.7885   1.0000
   3.500   0.6462   0.03270   0.02523  -0.0993   0.7843   1.0000
   3.750   0.6633   0.03340   0.02595  -0.0983   0.7724   1.0000
   4.000   0.7155   0.03282   0.02545  -0.1014   0.7677   1.0000
   4.250   0.7391   0.03315   0.02583  -0.1009   0.7560   1.0000
   4.500   0.7671   0.03328   0.02602  -0.1008   0.7448   1.0000
   4.750   0.8278   0.03167   0.02455  -0.1041   0.7400   1.0000
   5.000   0.8589   0.03134   0.02431  -0.1039   0.7282   1.0000
   5.250   0.9380   0.02839   0.02155  -0.1091   0.7245   1.0000
   5.500   0.9752   0.02742   0.02070  -0.1092   0.7122   1.0000
   5.750   1.0224   0.02586   0.01928  -0.1105   0.7010   1.0000
   6.000   1.0747   0.02398   0.01755  -0.1123   0.6891   1.0000
   6.250   1.1105   0.02283   0.01652  -0.1121   0.6723   1.0000
   6.500   1.1433   0.02177   0.01558  -0.1114   0.6525   1.0000
   6.750   1.1727   0.02083   0.01475  -0.1102   0.6288   1.0000
   7.000   1.1901   0.02038   0.01439  -0.1073   0.5980   1.0000
   7.250   1.2032   0.02010   0.01414  -0.1038   0.5544   1.0000
   7.500   1.2172   0.01995   0.01364  -0.1001   0.4790   1.0000
   7.750   1.2176   0.02098   0.01400  -0.0950   0.3926   1.0000
   8.000   1.2117   0.02265   0.01511  -0.0897   0.3234   1.0000
   8.250   1.2081   0.02447   0.01646  -0.0852   0.2712   1.0000
   8.500   1.2088   0.02628   0.01790  -0.0817   0.2314   1.0000
   8.750   1.2141   0.02802   0.01935  -0.0789   0.2016   1.0000
   9.000   1.2241   0.02966   0.02083  -0.0768   0.1782   1.0000
   9.250   1.2369   0.03124   0.02226  -0.0751   0.1599   1.0000
   9.500   1.2534   0.03280   0.02372  -0.0739   0.1449   1.0000
   9.750   1.2740   0.03436   0.02524  -0.0732   0.1322   1.0000
  10.000   1.2968   0.03597   0.02687  -0.0727   0.1214   1.0000
  10.250   1.3290   0.03784   0.02865  -0.0736   0.1119   1.0000
  10.500   1.3511   0.03946   0.03042  -0.0731   0.1044   1.0000
  10.750   1.3832   0.04174   0.03279  -0.0740   0.0973   1.0000
  11.000   1.4057   0.04372   0.03497  -0.0736   0.0919   1.0000
  11.250   1.4378   0.04664   0.03795  -0.0750   0.0863   1.0000
  11.500   1.4466   0.04888   0.04060  -0.0726   0.0830   1.0000
  11.750   1.4598   0.05120   0.04316  -0.0712   0.0795   1.0000
  12.000   1.4882   0.05511   0.04708  -0.0727   0.0749   1.0000
  12.250   1.4780   0.05736   0.04978  -0.0682   0.0737   1.0000
  12.500   1.4685   0.06031   0.05316  -0.0644   0.0725   1.0000
  12.750   1.4568   0.06352   0.05676  -0.0610   0.0712   1.0000
  13.000   1.4437   0.06692   0.06050  -0.0581   0.0699   1.0000
  13.250   1.4308   0.07041   0.06427  -0.0557   0.0685   1.0000
  13.500   1.4372   0.07295   0.06685  -0.0548   0.0658   1.0000
  13.750   1.4352   0.07694   0.07095  -0.0539   0.0642   1.0000
  14.000   1.4203   0.08256   0.07680  -0.0528   0.0635   1.0000
  14.500   1.3709   0.09347   0.08827  -0.0516   0.0633   1.0000
  14.750   1.3424   0.09879   0.09387  -0.0521   0.0636   1.0000
  15.000   1.2175   0.11818   0.11399  -0.0621   0.0723   1.0000
  15.250   1.1861   0.12870   0.12459  -0.0681   0.0737   1.0000
  15.500   1.1625   0.13916   0.13510  -0.0741   0.0747   1.0000
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