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S2062 8% (s2062-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S2062 8% (s2062-il)
Reynolds number: 50,000
Max Cl/Cd: 35.95 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2062-il-50000.txt
Download as CSV file: xf-s2062-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2062 8%                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4657   0.09594   0.08914  -0.0084   1.0000   0.2654
  -7.750  -0.4683   0.09317   0.08647  -0.0085   1.0000   0.2770
  -7.500  -0.4882   0.09217   0.08564  -0.0089   1.0000   0.2880
  -7.250  -0.4882   0.08914   0.08269  -0.0078   1.0000   0.3023
  -7.000  -0.4808   0.08556   0.07912  -0.0065   1.0000   0.3161
  -6.750  -0.4830   0.08264   0.07630  -0.0059   1.0000   0.3306
  -6.500  -0.4790   0.07913   0.07287  -0.0046   1.0000   0.3456
  -6.250  -0.5008   0.06238   0.05571  -0.0366   1.0000   0.1615
  -6.000  -0.4888   0.05467   0.04766  -0.0396   1.0000   0.1299
  -5.750  -0.4781   0.04834   0.04071  -0.0417   1.0000   0.1175
  -5.500  -0.4631   0.04396   0.03606  -0.0416   1.0000   0.1148
  -5.250  -0.4459   0.03953   0.03110  -0.0415   1.0000   0.1123
  -5.000  -0.4261   0.03574   0.02673  -0.0411   1.0000   0.1139
  -4.750  -0.4054   0.03272   0.02327  -0.0404   1.0000   0.1230
  -4.500  -0.3823   0.02984   0.01978  -0.0395   1.0000   0.1344
  -4.250  -0.3605   0.02774   0.01761  -0.0384   1.0000   0.1569
  -4.000  -0.3375   0.02573   0.01536  -0.0373   1.0000   0.1881
  -3.750  -0.3154   0.02400   0.01374  -0.0361   1.0000   0.2246
  -3.500  -0.2923   0.02242   0.01221  -0.0348   1.0000   0.2673
  -3.250  -0.2696   0.02097   0.01093  -0.0335   1.0000   0.3225
  -3.000  -0.2476   0.01954   0.00984  -0.0320   1.0000   0.4061
  -2.750  -0.2305   0.01788   0.00913  -0.0290   1.0000   0.5510
  -2.500  -0.2297   0.01680   0.00920  -0.0203   1.0000   0.7673
  -2.250  -0.1482   0.01632   0.00814  -0.0280   1.0000   1.0000
  -2.000  -0.1359   0.01617   0.00759  -0.0265   1.0000   1.0000
  -1.750  -0.1188   0.01613   0.00721  -0.0254   1.0000   1.0000
  -1.500  -0.0998   0.01616   0.00692  -0.0245   1.0000   1.0000
  -1.250  -0.0799   0.01622   0.00672  -0.0238   1.0000   1.0000
  -1.000  -0.0595   0.01633   0.00659  -0.0231   1.0000   1.0000
  -0.750  -0.0389   0.01647   0.00650  -0.0225   1.0000   1.0000
  -0.500  -0.0182   0.01665   0.00649  -0.0219   1.0000   1.0000
  -0.250   0.0025   0.01686   0.00655  -0.0213   1.0000   1.0000
   0.000   0.0232   0.01711   0.00666  -0.0208   1.0000   1.0000
   0.250   0.0437   0.01739   0.00683  -0.0203   1.0000   1.0000
   0.500   0.0639   0.01772   0.00704  -0.0199   1.0000   1.0000
   0.750   0.0840   0.01808   0.00734  -0.0195   1.0000   1.0000
   1.000   0.1036   0.01850   0.00769  -0.0191   1.0000   1.0000
   1.250   0.1230   0.01896   0.00812  -0.0188   1.0000   1.0000
   1.500   0.1419   0.01948   0.00862  -0.0185   1.0000   1.0000
   1.750   0.1604   0.02005   0.00919  -0.0183   1.0000   1.0000
   2.000   0.1784   0.02070   0.00984  -0.0182   1.0000   1.0000
   2.250   0.1958   0.02143   0.01059  -0.0181   1.0000   1.0000
   2.500   0.2126   0.02223   0.01144  -0.0181   1.0000   1.0000
   2.750   0.2688   0.02371   0.01306  -0.0255   0.9802   1.0000
   3.000   0.3332   0.02502   0.01457  -0.0338   0.9535   1.0000
   3.250   0.3945   0.02594   0.01577  -0.0408   0.9249   1.0000
   3.500   0.4532   0.02649   0.01660  -0.0465   0.8947   1.0000
   3.750   0.5137   0.02662   0.01707  -0.0516   0.8631   1.0000
   4.000   0.5855   0.02597   0.01693  -0.0571   0.8307   1.0000
   4.250   0.6360   0.02518   0.01652  -0.0582   0.7940   1.0000
   4.500   0.6847   0.02395   0.01569  -0.0578   0.7544   1.0000
   4.750   0.7229   0.02284   0.01483  -0.0554   0.7081   1.0000
   5.000   0.7530   0.02209   0.01417  -0.0519   0.6532   1.0000
   5.250   0.7778   0.02182   0.01379  -0.0480   0.5887   1.0000
   5.500   0.7963   0.02215   0.01393  -0.0440   0.5128   1.0000
   5.750   0.8111   0.02295   0.01430  -0.0401   0.4277   1.0000
   6.000   0.8214   0.02434   0.01507  -0.0361   0.3309   1.0000
   6.250   0.8273   0.02633   0.01626  -0.0323   0.2285   1.0000
   6.500   0.8425   0.02906   0.01837  -0.0301   0.1580   1.0000
   6.750   0.8684   0.03188   0.02089  -0.0291   0.1286   1.0000
   7.000   0.8970   0.03485   0.02402  -0.0285   0.1155   1.0000
   7.250   0.9206   0.03766   0.02731  -0.0272   0.1069   1.0000
   7.500   0.9424   0.04080   0.03062  -0.0264   0.1000   1.0000
   7.750   0.9605   0.04445   0.03490  -0.0248   0.0981   1.0000
   8.000   0.9746   0.04854   0.03956  -0.0231   0.0976   1.0000
   8.250   0.9847   0.05296   0.04451  -0.0215   0.0981   1.0000
   8.500   0.9911   0.05765   0.04965  -0.0200   0.0993   1.0000
   8.750   0.9975   0.06263   0.05494  -0.0188   0.1007   1.0000
   9.000   0.9827   0.06786   0.06086  -0.0172   0.1045   1.0000
   9.250   0.9579   0.07393   0.06734  -0.0167   0.1086   1.0000
   9.500   0.9438   0.07943   0.07298  -0.0167   0.1117   1.0000
   9.750   0.9520   0.08499   0.07860  -0.0167   0.1154   1.0000
  10.000   0.8802   0.09271   0.08640  -0.0227   0.1194   1.0000
  10.250   0.8621   0.10146   0.09509  -0.0284   0.1260   1.0000
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