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S2060 8% (s2060-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S2060 8% (s2060-il)
Reynolds number: 1,000,000
Max Cl/Cd: 79.01 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2060-il-1000000-n5.txt
Download as CSV file: xf-s2060-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.5785   0.11212   0.11039  -0.0112   1.0000   0.0034
 -11.750  -0.7104   0.07881   0.07706  -0.0281   1.0000   0.0032
 -11.500  -0.8675   0.04106   0.03911  -0.0569   1.0000   0.0029
 -11.250  -0.8788   0.03601   0.03381  -0.0584   1.0000   0.0029
 -11.000  -0.8862   0.03157   0.02906  -0.0582   1.0000   0.0029
 -10.750  -0.8821   0.02869   0.02592  -0.0574   1.0000   0.0030
 -10.500  -0.8726   0.02651   0.02352  -0.0563   1.0000   0.0030
 -10.250  -0.8607   0.02467   0.02146  -0.0551   1.0000   0.0031
 -10.000  -0.8480   0.02289   0.01946  -0.0538   1.0000   0.0031
  -9.750  -0.8337   0.02135   0.01772  -0.0525   1.0000   0.0032
  -9.500  -0.8116   0.01998   0.01617  -0.0525   0.9993   0.0033
  -9.250  -0.7839   0.01862   0.01460  -0.0535   0.9977   0.0033
  -9.000  -0.7553   0.01750   0.01331  -0.0546   0.9960   0.0034
  -8.750  -0.7257   0.01647   0.01213  -0.0557   0.9946   0.0035
  -8.500  -0.6976   0.01560   0.01111  -0.0563   0.9926   0.0035
  -8.250  -0.6691   0.01475   0.01011  -0.0570   0.9905   0.0036
  -8.000  -0.6397   0.01395   0.00920  -0.0578   0.9885   0.0036
  -7.750  -0.6102   0.01281   0.00788  -0.0588   0.9865   0.0039
  -7.500  -0.5791   0.01208   0.00705  -0.0598   0.9850   0.0042
  -7.250  -0.5473   0.01155   0.00645  -0.0610   0.9838   0.0045
  -7.000  -0.5191   0.01107   0.00589  -0.0612   0.9804   0.0048
  -6.750  -0.4901   0.01061   0.00536  -0.0616   0.9766   0.0051
  -6.500  -0.4600   0.01019   0.00488  -0.0622   0.9735   0.0054
  -6.250  -0.4289   0.00982   0.00444  -0.0630   0.9708   0.0058
  -6.000  -0.4013   0.00951   0.00408  -0.0630   0.9656   0.0060
  -5.750  -0.3724   0.00914   0.00364  -0.0633   0.9604   0.0068
  -5.500  -0.3428   0.00880   0.00328  -0.0637   0.9558   0.0083
  -5.250  -0.3156   0.00850   0.00297  -0.0636   0.9488   0.0117
  -5.000  -0.2874   0.00819   0.00269  -0.0637   0.9424   0.0200
  -4.750  -0.2602   0.00797   0.00248  -0.0636   0.9342   0.0253
  -4.500  -0.2327   0.00778   0.00227  -0.0634   0.9264   0.0301
  -4.250  -0.2054   0.00762   0.00209  -0.0633   0.9174   0.0340
  -4.000  -0.1781   0.00747   0.00192  -0.0631   0.9088   0.0387
  -3.750  -0.1510   0.00731   0.00177  -0.0629   0.8997   0.0466
  -3.500  -0.1238   0.00715   0.00161  -0.0627   0.8895   0.0564
  -3.250  -0.0966   0.00703   0.00147  -0.0625   0.8791   0.0645
  -3.000  -0.0693   0.00692   0.00135  -0.0623   0.8684   0.0730
  -2.750  -0.0422   0.00681   0.00123  -0.0621   0.8572   0.0863
  -2.500  -0.0149   0.00669   0.00112  -0.0620   0.8454   0.1015
  -2.250   0.0124   0.00658   0.00103  -0.0618   0.8332   0.1186
  -2.000   0.0396   0.00648   0.00094  -0.0616   0.8198   0.1392
  -1.750   0.0667   0.00634   0.00087  -0.0615   0.8051   0.1708
  -1.500   0.0937   0.00622   0.00079  -0.0613   0.7890   0.2066
  -1.250   0.1206   0.00611   0.00074  -0.0611   0.7717   0.2441
  -1.000   0.1476   0.00603   0.00069  -0.0609   0.7523   0.2800
  -0.750   0.1743   0.00591   0.00066  -0.0607   0.7313   0.3329
  -0.500   0.2009   0.00578   0.00064  -0.0605   0.7084   0.3933
  -0.250   0.2274   0.00569   0.00063  -0.0603   0.6842   0.4519
   0.000   0.2537   0.00559   0.00064  -0.0600   0.6585   0.5218
   0.250   0.2800   0.00550   0.00067  -0.0598   0.6315   0.5948
   0.500   0.3063   0.00549   0.00071  -0.0594   0.6029   0.6481
   0.750   0.3326   0.00554   0.00077  -0.0591   0.5735   0.6896
   1.000   0.3589   0.00560   0.00083  -0.0588   0.5434   0.7241
   1.250   0.3852   0.00569   0.00090  -0.0584   0.5130   0.7541
   1.500   0.4113   0.00581   0.00098  -0.0580   0.4800   0.7828
   1.750   0.4368   0.00594   0.00107  -0.0575   0.4441   0.8140
   2.000   0.4616   0.00607   0.00119  -0.0568   0.4067   0.8495
   2.250   0.4851   0.00631   0.00131  -0.0559   0.3553   0.8833
   2.500   0.5071   0.00659   0.00145  -0.0547   0.2991   0.9198
   2.750   0.5339   0.00683   0.00158  -0.0544   0.2531   0.9669
   3.000   0.5667   0.00719   0.00174  -0.0557   0.2056   1.0000
   3.250   0.5926   0.00750   0.00190  -0.0554   0.1720   1.0000
   3.500   0.6181   0.00785   0.00209  -0.0551   0.1371   1.0000
   3.750   0.6429   0.00830   0.00233  -0.0547   0.0914   1.0000
   4.000   0.6683   0.00869   0.00257  -0.0543   0.0613   1.0000
   4.250   0.6936   0.00909   0.00283  -0.0539   0.0352   1.0000
   4.500   0.7188   0.00951   0.00313  -0.0535   0.0156   1.0000
   4.750   0.7452   0.00975   0.00337  -0.0532   0.0128   1.0000
   5.000   0.7716   0.00998   0.00363  -0.0530   0.0121   1.0000
   5.250   0.7979   0.01023   0.00390  -0.0527   0.0115   1.0000
   5.500   0.8239   0.01052   0.00420  -0.0524   0.0109   1.0000
   5.750   0.8496   0.01084   0.00454  -0.0520   0.0101   1.0000
   6.000   0.8749   0.01122   0.00495  -0.0516   0.0094   1.0000
   6.250   0.8998   0.01166   0.00546  -0.0511   0.0089   1.0000
   6.500   0.9241   0.01220   0.00606  -0.0504   0.0086   1.0000
   6.750   0.9491   0.01259   0.00649  -0.0500   0.0085   1.0000
   7.000   0.9737   0.01301   0.00696  -0.0495   0.0084   1.0000
   7.250   0.9981   0.01346   0.00745  -0.0490   0.0082   1.0000
   7.500   1.0223   0.01393   0.00799  -0.0484   0.0081   1.0000
   7.750   1.0460   0.01444   0.00856  -0.0478   0.0079   1.0000
   8.000   1.0694   0.01498   0.00916  -0.0471   0.0077   1.0000
   8.250   1.0925   0.01555   0.00979  -0.0465   0.0074   1.0000
   8.500   1.1154   0.01611   0.01042  -0.0458   0.0071   1.0000
   8.750   1.1383   0.01665   0.01101  -0.0451   0.0068   1.0000
   9.000   1.1605   0.01728   0.01172  -0.0443   0.0066   1.0000
   9.250   1.1820   0.01796   0.01246  -0.0435   0.0064   1.0000
   9.500   1.2034   0.01862   0.01319  -0.0426   0.0062   1.0000
   9.750   1.2239   0.01936   0.01400  -0.0417   0.0060   1.0000
  10.000   1.2435   0.02018   0.01490  -0.0406   0.0059   1.0000
  10.250   1.2602   0.02132   0.01613  -0.0392   0.0056   1.0000
  10.500   1.2716   0.02309   0.01807  -0.0372   0.0054   1.0000
  10.750   1.2917   0.02365   0.01872  -0.0363   0.0053   1.0000
  11.000   1.3093   0.02446   0.01963  -0.0350   0.0052   1.0000
  11.250   1.3259   0.02530   0.02058  -0.0337   0.0051   1.0000
  11.500   1.3398   0.02636   0.02175  -0.0320   0.0051   1.0000
  11.750   1.3531   0.02733   0.02284  -0.0303   0.0049   1.0000
  12.000   1.3606   0.02847   0.02411  -0.0277   0.0048   1.0000
  12.250   1.3665   0.02962   0.02538  -0.0250   0.0047   1.0000
  12.500   1.3705   0.03093   0.02682  -0.0224   0.0046   1.0000
  12.750   1.3738   0.03234   0.02835  -0.0200   0.0045   1.0000
  13.000   1.3769   0.03382   0.02994  -0.0179   0.0044   1.0000
  13.250   1.3788   0.03550   0.03175  -0.0161   0.0043   1.0000
  13.500   1.3826   0.03710   0.03345  -0.0147   0.0042   1.0000
  13.750   1.3872   0.03872   0.03515  -0.0137   0.0040   1.0000
  14.000   1.3847   0.04122   0.03779  -0.0129   0.0040   1.0000
  14.250   1.3840   0.04373   0.04040  -0.0126   0.0039   1.0000
  14.500   1.3852   0.04622   0.04297  -0.0127   0.0038   1.0000
  14.750   1.3784   0.04997   0.04686  -0.0134   0.0038   1.0000
  15.000   1.3756   0.05353   0.05052  -0.0147   0.0038   1.0000
  15.250   1.3755   0.05695   0.05402  -0.0162   0.0037   1.0000
  15.500   1.3464   0.06556   0.06287  -0.0207   0.0037   1.0000
  15.750   1.3386   0.07114   0.06855  -0.0240   0.0037   1.0000
  16.000   1.2840   0.08665   0.08438  -0.0336   0.0038   1.0000
  16.250   1.2564   0.09749   0.09538  -0.0403   0.0038   1.0000
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