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S2062 8% (s2062-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S2062 8% (s2062-il)
Reynolds number: 100,000
Max Cl/Cd: 52.89 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2062-il-100000.txt
Download as CSV file: xf-s2062-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4806   0.09678   0.09181  -0.0193   1.0000   0.0990
  -8.500  -0.4860   0.09348   0.08859  -0.0220   1.0000   0.1031
  -8.250  -0.5145   0.09063   0.08592  -0.0294   1.0000   0.1050
  -8.000  -0.5085   0.08588   0.08121  -0.0284   1.0000   0.1067
  -7.750  -0.4872   0.08307   0.07836  -0.0242   1.0000   0.1119
  -7.500  -0.4961   0.07953   0.07491  -0.0274   1.0000   0.1162
  -7.250  -0.5233   0.07422   0.06950  -0.0393   1.0000   0.1194
  -7.000  -0.4980   0.07157   0.06704  -0.0311   1.0000   0.1237
  -6.750  -0.5112   0.06745   0.06269  -0.0388   1.0000   0.1327
  -6.500  -0.4971   0.06384   0.05928  -0.0344   1.0000   0.1366
  -6.250  -0.5015   0.04646   0.04078  -0.0439   1.0000   0.0639
  -6.000  -0.4910   0.04223   0.03638  -0.0432   1.0000   0.0617
  -5.750  -0.4791   0.03756   0.03128  -0.0425   1.0000   0.0591
  -5.500  -0.4628   0.03206   0.02462  -0.0413   1.0000   0.0534
  -5.250  -0.4428   0.02938   0.02144  -0.0400   1.0000   0.0528
  -5.000  -0.4225   0.02606   0.01768  -0.0390   1.0000   0.0534
  -4.750  -0.4009   0.02356   0.01499  -0.0380   1.0000   0.0560
  -4.500  -0.3782   0.02198   0.01317  -0.0369   1.0000   0.0621
  -4.250  -0.3555   0.02039   0.01145  -0.0359   1.0000   0.0729
  -4.000  -0.3322   0.01876   0.00975  -0.0348   1.0000   0.0941
  -3.750  -0.3100   0.01782   0.00889  -0.0341   1.0000   0.1307
  -3.500  -0.2875   0.01685   0.00806  -0.0333   1.0000   0.1656
  -3.250  -0.2646   0.01596   0.00731  -0.0325   1.0000   0.2049
  -3.000  -0.2420   0.01512   0.00672  -0.0318   1.0000   0.2607
  -2.750  -0.2200   0.01417   0.00630  -0.0310   1.0000   0.3511
  -2.500  -0.2002   0.01315   0.00610  -0.0296   1.0000   0.5114
  -2.250  -0.1881   0.01247   0.00627  -0.0254   1.0000   0.7183
  -2.000  -0.1780   0.01226   0.00637  -0.0202   1.0000   0.8704
  -1.750  -0.1290   0.01210   0.00599  -0.0241   1.0000   1.0000
  -1.500  -0.1082   0.01217   0.00582  -0.0236   1.0000   1.0000
  -1.250  -0.0870   0.01229   0.00572  -0.0231   1.0000   1.0000
  -1.000  -0.0657   0.01245   0.00570  -0.0226   1.0000   1.0000
  -0.750  -0.0443   0.01264   0.00571  -0.0222   1.0000   1.0000
  -0.500  -0.0231   0.01287   0.00580  -0.0217   1.0000   1.0000
  -0.250  -0.0021   0.01314   0.00595  -0.0213   1.0000   1.0000
   0.000   0.0187   0.01344   0.00615  -0.0209   1.0000   1.0000
   0.250   0.0503   0.01387   0.00648  -0.0227   0.9961   1.0000
   0.500   0.1005   0.01443   0.00697  -0.0278   0.9852   1.0000
   0.750   0.1490   0.01487   0.00736  -0.0325   0.9734   1.0000
   1.000   0.1966   0.01522   0.00769  -0.0369   0.9609   1.0000
   1.250   0.2440   0.01547   0.00795  -0.0410   0.9480   1.0000
   1.500   0.2916   0.01562   0.00814  -0.0450   0.9345   1.0000
   1.750   0.3396   0.01564   0.00824  -0.0488   0.9208   1.0000
   2.000   0.3889   0.01554   0.00822  -0.0526   0.9071   1.0000
   2.250   0.4380   0.01530   0.00811  -0.0561   0.8930   1.0000
   2.500   0.4824   0.01499   0.00794  -0.0583   0.8774   1.0000
   2.750   0.5236   0.01462   0.00769  -0.0597   0.8605   1.0000
   3.000   0.5584   0.01428   0.00747  -0.0597   0.8402   1.0000
   3.250   0.5904   0.01394   0.00726  -0.0591   0.8171   1.0000
   3.500   0.6183   0.01370   0.00709  -0.0577   0.7896   1.0000
   3.750   0.6450   0.01350   0.00693  -0.0561   0.7581   1.0000
   4.000   0.6697   0.01342   0.00688  -0.0543   0.7204   1.0000
   4.250   0.6939   0.01345   0.00691  -0.0524   0.6773   1.0000
   4.500   0.7167   0.01363   0.00700  -0.0505   0.6271   1.0000
   4.750   0.7384   0.01396   0.00718  -0.0485   0.5698   1.0000
   5.000   0.7585   0.01445   0.00745  -0.0464   0.5060   1.0000
   5.250   0.7762   0.01511   0.00781  -0.0442   0.4271   1.0000
   5.500   0.7919   0.01601   0.00822  -0.0420   0.3348   1.0000
   5.750   0.8086   0.01708   0.00888  -0.0403   0.2453   1.0000
   6.000   0.8185   0.01950   0.01035  -0.0378   0.1181   1.0000
   6.250   0.8333   0.02161   0.01211  -0.0356   0.0792   1.0000
   6.500   0.8527   0.02330   0.01376  -0.0340   0.0681   1.0000
   6.750   0.8742   0.02545   0.01582  -0.0329   0.0624   1.0000
   7.000   0.9001   0.02737   0.01793  -0.0320   0.0591   1.0000
   7.250   0.9260   0.02955   0.02031  -0.0312   0.0565   1.0000
   7.500   0.9492   0.03174   0.02258  -0.0306   0.0528   1.0000
   7.750   0.9712   0.03545   0.02652  -0.0299   0.0508   1.0000
   8.000   0.9905   0.03865   0.03018  -0.0285   0.0506   1.0000
   8.250   1.0067   0.04261   0.03457  -0.0270   0.0508   1.0000
   8.500   1.0221   0.04591   0.03834  -0.0253   0.0516   1.0000
   8.750   1.0213   0.05041   0.04395  -0.0215   0.0556   1.0000
   9.000   1.0191   0.05613   0.05020  -0.0193   0.0592   1.0000
   9.250   1.0214   0.06158   0.05589  -0.0181   0.0618   1.0000
   9.500   0.9333   0.05875   0.05398  -0.0108   0.0664   1.0000
   9.750   0.8975   0.06377   0.05924  -0.0086   0.0677   1.0000
  10.000   0.8648   0.06915   0.06477  -0.0089   0.0682   1.0000
  10.250   0.8310   0.07592   0.07165  -0.0117   0.0682   1.0000
  10.500   0.7923   0.08553   0.08134  -0.0179   0.0686   1.0000
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