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S2060 8% (s2060-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S2060 8% (s2060-il)
Reynolds number: 200,000
Max Cl/Cd: 62.89 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2060-il-200000-n5.txt
Download as CSV file: xf-s2060-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2060 8%                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5217   0.08696   0.08333  -0.0244   1.0000   0.0118
  -9.250  -0.5282   0.08163   0.07806  -0.0270   1.0000   0.0117
  -9.000  -0.5378   0.07591   0.07240  -0.0301   1.0000   0.0116
  -8.750  -0.5536   0.06947   0.06606  -0.0338   1.0000   0.0113
  -8.250  -0.6411   0.03784   0.03365  -0.0509   1.0000   0.0102
  -8.000  -0.6405   0.03284   0.02811  -0.0503   1.0000   0.0103
  -7.750  -0.6318   0.02932   0.02412  -0.0493   1.0000   0.0104
  -7.500  -0.6186   0.02667   0.02107  -0.0481   1.0000   0.0108
  -7.250  -0.6029   0.02441   0.01844  -0.0469   1.0000   0.0112
  -7.000  -0.5854   0.02254   0.01623  -0.0457   1.0000   0.0117
  -6.750  -0.5666   0.02090   0.01426  -0.0445   1.0000   0.0124
  -6.500  -0.5466   0.01968   0.01277  -0.0434   1.0000   0.0134
  -6.250  -0.5264   0.01865   0.01163  -0.0425   1.0000   0.0148
  -6.000  -0.5054   0.01784   0.01071  -0.0415   1.0000   0.0161
  -5.750  -0.4840   0.01688   0.00958  -0.0405   1.0000   0.0178
  -5.500  -0.4556   0.01591   0.00851  -0.0410   0.9982   0.0209
  -5.250  -0.4224   0.01518   0.00763  -0.0423   0.9952   0.0266
  -5.000  -0.3896   0.01480   0.00718  -0.0436   0.9918   0.0348
  -4.750  -0.3567   0.01441   0.00678  -0.0450   0.9881   0.0441
  -4.500  -0.3229   0.01401   0.00634  -0.0465   0.9849   0.0526
  -4.250  -0.2900   0.01363   0.00583  -0.0477   0.9812   0.0597
  -4.000  -0.2582   0.01315   0.00535  -0.0488   0.9766   0.0673
  -3.750  -0.2242   0.01275   0.00494  -0.0502   0.9729   0.0776
  -3.500  -0.1892   0.01239   0.00457  -0.0519   0.9697   0.0911
  -3.250  -0.1590   0.01205   0.00424  -0.0525   0.9638   0.1076
  -3.000  -0.1248   0.01170   0.00397  -0.0540   0.9596   0.1355
  -2.750  -0.0886   0.01132   0.00372  -0.0560   0.9565   0.1743
  -2.500  -0.0593   0.01095   0.00353  -0.0565   0.9497   0.2249
  -2.250  -0.0260   0.01052   0.00333  -0.0578   0.9449   0.2938
  -2.000   0.0050   0.01008   0.00319  -0.0587   0.9390   0.3789
  -1.750   0.0347   0.00959   0.00309  -0.0592   0.9321   0.4843
  -1.500   0.0642   0.00916   0.00304  -0.0594   0.9256   0.5946
  -1.250   0.0921   0.00888   0.00302  -0.0590   0.9173   0.6787
  -1.000   0.1197   0.00868   0.00299  -0.0585   0.9087   0.7399
  -0.750   0.1482   0.00850   0.00293  -0.0580   0.9006   0.7905
  -0.500   0.1736   0.00838   0.00289  -0.0569   0.8898   0.8352
  -0.250   0.2011   0.00827   0.00283  -0.0561   0.8791   0.8769
   0.000   0.2329   0.00817   0.00275  -0.0564   0.8683   0.9166
   0.250   0.2716   0.00807   0.00264  -0.0582   0.8566   0.9536
   0.500   0.3137   0.00799   0.00252  -0.0610   0.8430   0.9886
   0.750   0.3441   0.00799   0.00246  -0.0614   0.8264   1.0000
   1.000   0.3698   0.00802   0.00243  -0.0608   0.8081   1.0000
   1.250   0.3957   0.00807   0.00241  -0.0602   0.7886   1.0000
   1.500   0.4215   0.00814   0.00240  -0.0595   0.7668   1.0000
   1.750   0.4472   0.00823   0.00240  -0.0589   0.7429   1.0000
   2.000   0.4727   0.00835   0.00244  -0.0581   0.7160   1.0000
   2.250   0.4980   0.00850   0.00249  -0.0574   0.6862   1.0000
   2.500   0.5230   0.00868   0.00256  -0.0566   0.6533   1.0000
   2.750   0.5475   0.00892   0.00265  -0.0558   0.6176   1.0000
   3.000   0.5718   0.00918   0.00279  -0.0549   0.5786   1.0000
   3.250   0.5957   0.00950   0.00295  -0.0541   0.5365   1.0000
   3.500   0.6195   0.00985   0.00314  -0.0532   0.4937   1.0000
   3.750   0.6431   0.01023   0.00336  -0.0524   0.4507   1.0000
   4.000   0.6658   0.01071   0.00364  -0.0515   0.3970   1.0000
   4.250   0.6870   0.01136   0.00395  -0.0505   0.3251   1.0000
   4.500   0.7085   0.01206   0.00430  -0.0496   0.2559   1.0000
   4.750   0.7309   0.01272   0.00469  -0.0488   0.1994   1.0000
   5.000   0.7543   0.01329   0.00513  -0.0482   0.1598   1.0000
   5.250   0.7764   0.01405   0.00563  -0.0475   0.1098   1.0000
   5.500   0.7987   0.01481   0.00619  -0.0468   0.0690   1.0000
   5.750   0.8200   0.01575   0.00691  -0.0459   0.0354   1.0000
   6.000   0.8427   0.01650   0.00763  -0.0451   0.0262   1.0000
   6.250   0.8661   0.01713   0.00837  -0.0444   0.0235   1.0000
   6.500   0.8890   0.01783   0.00920  -0.0436   0.0216   1.0000
   6.750   0.9109   0.01865   0.01011  -0.0426   0.0202   1.0000
   7.000   0.9310   0.01969   0.01125  -0.0415   0.0192   1.0000
   7.250   0.9510   0.02076   0.01242  -0.0403   0.0187   1.0000
   7.500   0.9715   0.02176   0.01355  -0.0392   0.0181   1.0000
   7.750   0.9921   0.02278   0.01469  -0.0382   0.0172   1.0000
   8.000   1.0124   0.02385   0.01591  -0.0372   0.0163   1.0000
   8.250   1.0320   0.02514   0.01733  -0.0361   0.0157   1.0000
   8.500   1.0512   0.02656   0.01889  -0.0349   0.0153   1.0000
   8.750   1.0700   0.02809   0.02058  -0.0338   0.0148   1.0000
   9.000   1.0880   0.02978   0.02244  -0.0326   0.0145   1.0000
   9.250   1.1048   0.03164   0.02450  -0.0314   0.0141   1.0000
   9.500   1.1198   0.03379   0.02690  -0.0300   0.0138   1.0000
   9.750   1.1319   0.03630   0.02968  -0.0285   0.0135   1.0000
  10.000   1.1357   0.04019   0.03391  -0.0264   0.0130   1.0000
  10.250   1.1425   0.04203   0.03611  -0.0243   0.0127   1.0000
  10.500   1.1445   0.04438   0.03880  -0.0219   0.0124   1.0000
  10.750   1.1389   0.04702   0.04175  -0.0189   0.0122   1.0000
  11.000   1.1283   0.05000   0.04502  -0.0160   0.0121   1.0000
  11.250   1.1149   0.05335   0.04864  -0.0140   0.0120   1.0000
  11.500   1.0992   0.05723   0.05277  -0.0130   0.0120   1.0000
  11.750   1.0812   0.06182   0.05760  -0.0135   0.0120   1.0000
  12.000   1.0621   0.06727   0.06326  -0.0155   0.0120   1.0000
  12.250   1.0413   0.07391   0.07011  -0.0193   0.0120   1.0000
  12.500   1.0203   0.08175   0.07812  -0.0247   0.0121   1.0000
  12.750   0.9980   0.09124   0.08776  -0.0317   0.0123   1.0000
  13.000   0.9728   0.10291   0.09956  -0.0399   0.0124   1.0000
  13.250   0.9466   0.11590   0.11261  -0.0480   0.0127   1.0000
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