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S2060 8% (s2060-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S2060 8% (s2060-il)
Reynolds number: 500,000
Max Cl/Cd: 75.1 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2060-il-500000-n5.txt
Download as CSV file: xf-s2060-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5593   0.09157   0.08923  -0.0208   1.0000   0.0058
 -10.250  -0.5763   0.08382   0.08152  -0.0246   1.0000   0.0058
  -9.750  -0.7631   0.03517   0.03229  -0.0549   1.0000   0.0046
  -9.500  -0.7643   0.03100   0.02773  -0.0543   1.0000   0.0047
  -9.250  -0.7585   0.02786   0.02423  -0.0532   1.0000   0.0048
  -9.000  -0.7478   0.02551   0.02157  -0.0519   1.0000   0.0049
  -8.750  -0.7339   0.02369   0.01948  -0.0506   1.0000   0.0050
  -8.500  -0.7181   0.02223   0.01778  -0.0494   1.0000   0.0053
  -8.250  -0.7018   0.02075   0.01605  -0.0480   1.0000   0.0054
  -8.000  -0.6751   0.01940   0.01446  -0.0487   0.9985   0.0057
  -7.750  -0.6455   0.01804   0.01286  -0.0499   0.9963   0.0058
  -7.500  -0.6151   0.01682   0.01143  -0.0510   0.9944   0.0059
  -7.250  -0.5866   0.01555   0.00996  -0.0518   0.9918   0.0061
  -7.000  -0.5572   0.01436   0.00859  -0.0527   0.9891   0.0066
  -6.750  -0.5261   0.01355   0.00763  -0.0537   0.9867   0.0071
  -6.500  -0.4939   0.01291   0.00690  -0.0549   0.9848   0.0076
  -6.250  -0.4616   0.01234   0.00622  -0.0561   0.9829   0.0083
  -6.000  -0.4326   0.01186   0.00564  -0.0565   0.9790   0.0089
  -5.750  -0.4014   0.01133   0.00506  -0.0574   0.9760   0.0107
  -5.500  -0.3692   0.01084   0.00456  -0.0585   0.9735   0.0156
  -5.250  -0.3364   0.01045   0.00419  -0.0597   0.9712   0.0229
  -5.000  -0.3066   0.01016   0.00388  -0.0602   0.9671   0.0282
  -4.750  -0.2767   0.00990   0.00362  -0.0607   0.9623   0.0336
  -4.500  -0.2450   0.00964   0.00332  -0.0615   0.9586   0.0391
  -4.250  -0.2143   0.00942   0.00311  -0.0622   0.9541   0.0469
  -4.000  -0.1855   0.00914   0.00287  -0.0624   0.9478   0.0555
  -3.750  -0.1543   0.00891   0.00262  -0.0631   0.9429   0.0627
  -3.500  -0.1261   0.00871   0.00240  -0.0631   0.9356   0.0717
  -3.250  -0.0965   0.00848   0.00220  -0.0635   0.9293   0.0852
  -3.000  -0.0686   0.00827   0.00203  -0.0635   0.9212   0.1010
  -2.750  -0.0400   0.00807   0.00186  -0.0636   0.9135   0.1202
  -2.500  -0.0127   0.00786   0.00171  -0.0634   0.9038   0.1457
  -2.250   0.0147   0.00764   0.00158  -0.0633   0.8940   0.1804
  -2.000   0.0420   0.00742   0.00147  -0.0632   0.8840   0.2205
  -1.750   0.0689   0.00720   0.00137  -0.0630   0.8730   0.2701
  -1.500   0.0958   0.00699   0.00128  -0.0628   0.8613   0.3203
  -1.250   0.1224   0.00674   0.00120  -0.0626   0.8488   0.3875
  -1.000   0.1488   0.00647   0.00115  -0.0623   0.8354   0.4651
  -0.750   0.1749   0.00623   0.00111  -0.0619   0.8208   0.5452
  -0.500   0.2008   0.00604   0.00111  -0.0614   0.8052   0.6214
  -0.250   0.2267   0.00593   0.00112  -0.0608   0.7882   0.6785
   0.000   0.2527   0.00587   0.00113  -0.0602   0.7696   0.7211
   0.250   0.2784   0.00584   0.00114  -0.0595   0.7489   0.7589
   0.500   0.3036   0.00584   0.00116  -0.0588   0.7267   0.7936
   0.750   0.3285   0.00587   0.00119  -0.0579   0.7020   0.8255
   1.250   0.3759   0.00596   0.00128  -0.0555   0.6477   0.8939
   1.500   0.4006   0.00605   0.00132  -0.0546   0.6179   0.9330
   1.750   0.4334   0.00619   0.00136  -0.0555   0.5835   0.9686
   2.250   0.4930   0.00665   0.00152  -0.0565   0.5075   1.0000
   2.500   0.5180   0.00692   0.00163  -0.0560   0.4685   1.0000
   2.750   0.5430   0.00723   0.00176  -0.0555   0.4266   1.0000
   3.000   0.5668   0.00768   0.00194  -0.0549   0.3640   1.0000
   3.250   0.5906   0.00818   0.00214  -0.0543   0.2993   1.0000
   3.500   0.6150   0.00864   0.00235  -0.0538   0.2460   1.0000
   3.750   0.6402   0.00900   0.00256  -0.0534   0.2097   1.0000
   4.000   0.6647   0.00945   0.00283  -0.0530   0.1655   1.0000
   4.250   0.6894   0.00990   0.00310  -0.0525   0.1271   1.0000
   4.500   0.7135   0.01043   0.00342  -0.0520   0.0861   1.0000
   5.000   0.7615   0.01155   0.00422  -0.0509   0.0234   1.0000
   5.250   0.7867   0.01195   0.00459  -0.0505   0.0172   1.0000
   5.500   0.8120   0.01232   0.00498  -0.0500   0.0154   1.0000
   5.750   0.8370   0.01274   0.00544  -0.0495   0.0140   1.0000
   6.000   0.8615   0.01326   0.00604  -0.0489   0.0130   1.0000
   6.250   0.8862   0.01370   0.00655  -0.0484   0.0127   1.0000
   6.500   0.9106   0.01416   0.00708  -0.0479   0.0122   1.0000
   6.750   0.9346   0.01467   0.00765  -0.0473   0.0116   1.0000
   7.000   0.9580   0.01526   0.00831  -0.0466   0.0113   1.0000
   7.250   0.9810   0.01590   0.00902  -0.0458   0.0110   1.0000
   7.500   1.0034   0.01658   0.00978  -0.0450   0.0106   1.0000
   7.750   1.0254   0.01732   0.01061  -0.0441   0.0103   1.0000
   8.000   1.0469   0.01810   0.01147  -0.0432   0.0100   1.0000
   8.250   1.0677   0.01896   0.01242  -0.0423   0.0097   1.0000
   8.500   1.0875   0.01996   0.01351  -0.0412   0.0094   1.0000
   8.750   1.1056   0.02121   0.01487  -0.0399   0.0090   1.0000
   9.000   1.1199   0.02326   0.01708  -0.0381   0.0085   1.0000
   9.250   1.1402   0.02410   0.01807  -0.0372   0.0084   1.0000
   9.500   1.1593   0.02508   0.01919  -0.0361   0.0082   1.0000
   9.750   1.1766   0.02634   0.02062  -0.0348   0.0080   1.0000
  10.000   1.1928   0.02768   0.02213  -0.0334   0.0078   1.0000
  10.250   1.2071   0.02919   0.02383  -0.0318   0.0076   1.0000
  10.500   1.2194   0.03082   0.02567  -0.0301   0.0074   1.0000
  10.750   1.2296   0.03251   0.02755  -0.0282   0.0072   1.0000
  11.000   1.2369   0.03423   0.02948  -0.0260   0.0070   1.0000
  11.250   1.2405   0.03575   0.03118  -0.0233   0.0068   1.0000
  11.500   1.2414   0.03741   0.03301  -0.0205   0.0066   1.0000
  11.750   1.2429   0.03889   0.03462  -0.0182   0.0064   1.0000
  12.000   1.2416   0.04080   0.03667  -0.0161   0.0062   1.0000
  12.250   1.2394   0.04289   0.03889  -0.0146   0.0061   1.0000
  12.500   1.2339   0.04556   0.04173  -0.0134   0.0060   1.0000
  12.750   1.2306   0.04814   0.04442  -0.0130   0.0059   1.0000
  13.000   1.2239   0.05143   0.04784  -0.0132   0.0058   1.0000
  13.250   1.2100   0.05622   0.05283  -0.0145   0.0058   1.0000
  13.500   1.1967   0.06144   0.05822  -0.0168   0.0058   1.0000
  13.750   1.1806   0.06783   0.06479  -0.0204   0.0058   1.0000
  14.000   1.1609   0.07571   0.07287  -0.0254   0.0058   1.0000
  14.250   1.1409   0.08451   0.08184  -0.0312   0.0058   1.0000
  14.500   1.1006   0.09922   0.09682  -0.0409   0.0059   1.0000
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