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S2062 8% (s2062-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S2062 8% (s2062-il)
Reynolds number: 500,000
Max Cl/Cd: 74.6 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2062-il-500000-n5.txt
Download as CSV file: xf-s2062-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4431   0.08191   0.07974  -0.0237   1.0000   0.0051
  -9.750  -0.4522   0.07568   0.07354  -0.0257   1.0000   0.0052
  -9.500  -0.4722   0.06707   0.06496  -0.0287   1.0000   0.0050
  -9.250  -0.5380   0.04953   0.04750  -0.0359   1.0000   0.0046
  -8.750  -0.6598   0.03983   0.03722  -0.0491   1.0000   0.0040
  -8.500  -0.6735   0.03323   0.03011  -0.0489   1.0000   0.0041
  -8.250  -0.6751   0.02865   0.02505  -0.0474   1.0000   0.0041
  -8.000  -0.6698   0.02513   0.02108  -0.0456   1.0000   0.0043
  -7.750  -0.6515   0.02264   0.01822  -0.0454   0.9990   0.0044
  -7.500  -0.6233   0.02064   0.01592  -0.0468   0.9965   0.0046
  -7.250  -0.5934   0.01912   0.01416  -0.0482   0.9943   0.0048
  -7.000  -0.5651   0.01773   0.01254  -0.0489   0.9915   0.0050
  -6.750  -0.5349   0.01689   0.01156  -0.0500   0.9888   0.0054
  -6.500  -0.5039   0.01592   0.01042  -0.0511   0.9864   0.0058
  -6.250  -0.4722   0.01492   0.00926  -0.0522   0.9844   0.0061
  -6.000  -0.4416   0.01391   0.00806  -0.0531   0.9819   0.0063
  -5.750  -0.4126   0.01303   0.00705  -0.0536   0.9780   0.0065
  -5.500  -0.3814   0.01229   0.00619  -0.0545   0.9749   0.0067
  -5.250  -0.3491   0.01168   0.00548  -0.0556   0.9723   0.0069
  -5.000  -0.3166   0.01093   0.00460  -0.0567   0.9699   0.0078
  -4.750  -0.2890   0.01049   0.00407  -0.0567   0.9641   0.0087
  -4.500  -0.2582   0.01010   0.00362  -0.0573   0.9598   0.0101
  -4.250  -0.2262   0.00969   0.00320  -0.0583   0.9563   0.0161
  -4.000  -0.1989   0.00927   0.00288  -0.0582   0.9494   0.0357
  -3.750  -0.1684   0.00896   0.00262  -0.0588   0.9441   0.0531
  -3.500  -0.1397   0.00869   0.00239  -0.0591   0.9373   0.0716
  -3.250  -0.1108   0.00839   0.00219  -0.0594   0.9303   0.0998
  -3.000  -0.0830   0.00810   0.00202  -0.0594   0.9222   0.1322
  -2.500  -0.0273   0.00767   0.00170  -0.0594   0.9049   0.1907
  -2.250   0.0001   0.00744   0.00157  -0.0593   0.8957   0.2297
  -2.000   0.0273   0.00725   0.00145  -0.0591   0.8856   0.2681
  -1.750   0.0541   0.00703   0.00135  -0.0589   0.8742   0.3178
  -1.500   0.0808   0.00681   0.00126  -0.0587   0.8623   0.3703
  -1.250   0.1074   0.00659   0.00119  -0.0584   0.8502   0.4309
  -1.000   0.1338   0.00637   0.00114  -0.0581   0.8372   0.4976
  -0.750   0.1598   0.00613   0.00110  -0.0577   0.8227   0.5728
  -0.500   0.1853   0.00591   0.00109  -0.0571   0.8070   0.6515
  -0.250   0.2106   0.00578   0.00110  -0.0564   0.7898   0.7182
   0.000   0.2361   0.00572   0.00112  -0.0557   0.7713   0.7645
   0.250   0.2616   0.00571   0.00113  -0.0549   0.7509   0.7988
   0.500   0.2868   0.00574   0.00115  -0.0541   0.7290   0.8272
   0.750   0.3115   0.00578   0.00118  -0.0532   0.7049   0.8539
   1.000   0.3359   0.00584   0.00121  -0.0522   0.6793   0.8800
   1.250   0.3600   0.00592   0.00125  -0.0512   0.6520   0.9046
   1.500   0.3847   0.00604   0.00129  -0.0503   0.6225   0.9292
   1.750   0.4133   0.00618   0.00134  -0.0503   0.5896   0.9554
   2.000   0.4478   0.00638   0.00140  -0.0517   0.5506   0.9806
   2.250   0.4801   0.00661   0.00149  -0.0529   0.5103   1.0000
   2.500   0.5048   0.00688   0.00159  -0.0523   0.4712   1.0000
   2.750   0.5299   0.00715   0.00172  -0.0518   0.4353   1.0000
   3.000   0.5550   0.00744   0.00188  -0.0514   0.3979   1.0000
   3.250   0.5785   0.00792   0.00207  -0.0507   0.3322   1.0000
   3.500   0.6012   0.00855   0.00231  -0.0500   0.2512   1.0000
   3.750   0.6248   0.00911   0.00256  -0.0495   0.1881   1.0000
   4.000   0.6494   0.00955   0.00281  -0.0491   0.1464   1.0000
   4.250   0.6743   0.00996   0.00310  -0.0487   0.1132   1.0000
   4.500   0.6984   0.01049   0.00343  -0.0482   0.0730   1.0000
   4.750   0.7226   0.01102   0.00380  -0.0477   0.0411   1.0000
   5.000   0.7468   0.01156   0.00421  -0.0471   0.0196   1.0000
   5.250   0.7722   0.01193   0.00459  -0.0467   0.0158   1.0000
   5.500   0.7977   0.01228   0.00502  -0.0463   0.0148   1.0000
   5.750   0.8229   0.01267   0.00546  -0.0459   0.0139   1.0000
   6.000   0.8478   0.01309   0.00594  -0.0454   0.0130   1.0000
   6.250   0.8723   0.01356   0.00646  -0.0449   0.0123   1.0000
   6.500   0.8963   0.01411   0.00707  -0.0443   0.0118   1.0000
   6.750   0.9196   0.01474   0.00778  -0.0435   0.0113   1.0000
   7.000   0.9416   0.01554   0.00870  -0.0427   0.0108   1.0000
   7.250   0.9614   0.01667   0.00995  -0.0414   0.0103   1.0000
   7.500   0.9838   0.01739   0.01076  -0.0406   0.0102   1.0000
   7.750   1.0056   0.01819   0.01165  -0.0397   0.0100   1.0000
   8.000   1.0274   0.01899   0.01255  -0.0389   0.0097   1.0000
   8.250   1.0490   0.01978   0.01344  -0.0380   0.0093   1.0000
   8.500   1.0700   0.02066   0.01446  -0.0371   0.0089   1.0000
   8.750   1.0899   0.02174   0.01566  -0.0360   0.0086   1.0000
   9.000   1.1092   0.02287   0.01693  -0.0349   0.0083   1.0000
   9.250   1.1279   0.02408   0.01829  -0.0338   0.0080   1.0000
   9.500   1.1459   0.02530   0.01966  -0.0326   0.0077   1.0000
   9.750   1.1636   0.02636   0.02083  -0.0315   0.0074   1.0000
  10.000   1.1805   0.02735   0.02192  -0.0303   0.0071   1.0000
  10.250   1.1946   0.02870   0.02340  -0.0289   0.0068   1.0000
  10.500   1.1968   0.03187   0.02686  -0.0263   0.0063   1.0000
  10.750   1.2083   0.03314   0.02833  -0.0245   0.0062   1.0000
  11.000   1.2158   0.03458   0.02996  -0.0223   0.0061   1.0000
  11.250   1.2178   0.03623   0.03182  -0.0194   0.0059   1.0000
  11.500   1.2147   0.03836   0.03416  -0.0164   0.0058   1.0000
  11.750   1.2101   0.04065   0.03667  -0.0139   0.0056   1.0000
  12.000   1.2031   0.04332   0.03956  -0.0120   0.0055   1.0000
  12.250   1.1912   0.04676   0.04321  -0.0107   0.0054   1.0000
  12.500   1.1782   0.05067   0.04734  -0.0105   0.0053   1.0000
  12.750   1.1634   0.05531   0.05219  -0.0115   0.0052   1.0000
  13.000   1.1458   0.06107   0.05815  -0.0140   0.0052   1.0000
  13.250   1.1268   0.06797   0.06524  -0.0181   0.0052   1.0000
  13.500   1.1035   0.07680   0.07426  -0.0240   0.0053   1.0000
  13.750   1.0826   0.08630   0.08392  -0.0306   0.0053   1.0000
  14.000   1.0550   0.09830   0.09607  -0.0385   0.0055   1.0000
  14.250   1.0222   0.11250   0.11039  -0.0472   0.0057   1.0000
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