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S2060 8% (s2060-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S2060 8% (s2060-il)
Reynolds number: 200,000
Max Cl/Cd: 70.85 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2060-il-200000.txt
Download as CSV file: xf-s2060-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3943   0.08735   0.08394  -0.0248   1.0000   0.0519
  -9.000  -0.4024   0.08264   0.07927  -0.0278   1.0000   0.0538
  -8.750  -0.4162   0.07764   0.07434  -0.0324   1.0000   0.0548
  -8.500  -0.4276   0.07255   0.06931  -0.0361   1.0000   0.0551
  -8.250  -0.4406   0.06746   0.06427  -0.0399   1.0000   0.0551
  -8.000  -0.4564   0.06261   0.05941  -0.0430   1.0000   0.0552
  -7.750  -0.4694   0.05780   0.05452  -0.0448   1.0000   0.0552
  -7.500  -0.5198   0.06498   0.06136  -0.0458   1.0000   0.0551
  -7.250  -0.5211   0.06089   0.05708  -0.0464   1.0000   0.0553
  -7.000  -0.5376   0.04435   0.04031  -0.0471   1.0000   0.0313
  -6.750  -0.5357   0.03911   0.03476  -0.0465   1.0000   0.0298
  -6.500  -0.5312   0.03304   0.02813  -0.0455   1.0000   0.0282
  -6.250  -0.5196   0.02839   0.02287  -0.0443   1.0000   0.0280
  -6.000  -0.5023   0.02616   0.02025  -0.0431   1.0000   0.0302
  -5.750  -0.4834   0.02371   0.01729  -0.0418   1.0000   0.0316
  -5.500  -0.4625   0.02175   0.01488  -0.0405   1.0000   0.0326
  -5.250  -0.4417   0.01885   0.01171  -0.0397   1.0000   0.0354
  -5.000  -0.4195   0.01794   0.01066  -0.0387   1.0000   0.0406
  -4.750  -0.3973   0.01686   0.00948  -0.0379   1.0000   0.0485
  -4.500  -0.3745   0.01597   0.00844  -0.0370   1.0000   0.0580
  -4.250  -0.3519   0.01582   0.00819  -0.0362   1.0000   0.0678
  -4.000  -0.3290   0.01500   0.00741  -0.0356   1.0000   0.0774
  -3.750  -0.3059   0.01435   0.00671  -0.0349   1.0000   0.0862
  -3.500  -0.2827   0.01396   0.00624  -0.0341   1.0000   0.0954
  -3.250  -0.2598   0.01347   0.00579  -0.0335   1.0000   0.1082
  -3.000  -0.2367   0.01294   0.00534  -0.0329   1.0000   0.1246
  -2.750  -0.2138   0.01254   0.00503  -0.0324   1.0000   0.1509
  -2.500  -0.1817   0.01200   0.00481  -0.0339   0.9975   0.2083
  -2.250  -0.1438   0.01134   0.00474  -0.0366   0.9932   0.3399
  -2.000  -0.1091   0.01060   0.00480  -0.0386   0.9879   0.5359
  -1.750  -0.0744   0.01026   0.00507  -0.0397   0.9830   0.7061
  -1.500  -0.0446   0.01007   0.00515  -0.0395   0.9754   0.8029
  -1.250  -0.0078   0.01000   0.00524  -0.0404   0.9706   0.8911
  -1.000   0.0503   0.00985   0.00507  -0.0463   0.9680   1.0000
  -0.750   0.0908   0.00986   0.00496  -0.0491   0.9606   1.0000
  -0.500   0.1388   0.00986   0.00486  -0.0533   0.9564   1.0000
  -0.250   0.1752   0.00979   0.00473  -0.0551   0.9470   1.0000
   0.000   0.2250   0.00967   0.00456  -0.0594   0.9428   1.0000
   0.250   0.2617   0.00956   0.00441  -0.0611   0.9331   1.0000
   0.500   0.3046   0.00938   0.00421  -0.0639   0.9265   1.0000
   0.750   0.3399   0.00922   0.00404  -0.0650   0.9161   1.0000
   1.000   0.3717   0.00908   0.00390  -0.0654   0.9041   1.0000
   1.250   0.4022   0.00895   0.00377  -0.0654   0.8913   1.0000
   1.500   0.4309   0.00884   0.00365  -0.0651   0.8769   1.0000
   1.750   0.4584   0.00876   0.00355  -0.0644   0.8611   1.0000
   2.000   0.4854   0.00870   0.00349  -0.0637   0.8440   1.0000
   2.250   0.5108   0.00868   0.00346  -0.0626   0.8235   1.0000
   2.500   0.5366   0.00868   0.00343  -0.0617   0.8016   1.0000
   2.750   0.5618   0.00872   0.00343  -0.0606   0.7760   1.0000
   3.000   0.5869   0.00878   0.00347  -0.0596   0.7473   1.0000
   3.250   0.6117   0.00890   0.00350  -0.0585   0.7152   1.0000
   3.500   0.6360   0.00907   0.00359  -0.0574   0.6783   1.0000
   3.750   0.6600   0.00932   0.00371  -0.0563   0.6375   1.0000
   4.000   0.6830   0.00964   0.00388  -0.0550   0.5891   1.0000
   4.250   0.7052   0.01005   0.00408  -0.0537   0.5334   1.0000
   4.500   0.7256   0.01061   0.00432  -0.0521   0.4616   1.0000
   4.750   0.7456   0.01127   0.00463  -0.0507   0.3873   1.0000
   5.000   0.7664   0.01195   0.00503  -0.0496   0.3187   1.0000
   5.250   0.7875   0.01267   0.00547  -0.0486   0.2542   1.0000
   5.500   0.8085   0.01349   0.00599  -0.0477   0.1892   1.0000
   5.750   0.8243   0.01516   0.00692  -0.0461   0.0754   1.0000
   6.000   0.8428   0.01661   0.00818  -0.0445   0.0466   1.0000
   6.250   0.8628   0.01778   0.00943  -0.0431   0.0410   1.0000
   6.500   0.8838   0.01882   0.01055  -0.0419   0.0378   1.0000
   6.750   0.9043   0.02003   0.01179  -0.0407   0.0356   1.0000
   7.000   0.9234   0.02199   0.01375  -0.0393   0.0333   1.0000
   7.250   0.9463   0.02333   0.01522  -0.0384   0.0318   1.0000
   7.500   0.9698   0.02495   0.01702  -0.0375   0.0310   1.0000
   7.750   0.9931   0.02689   0.01917  -0.0366   0.0303   1.0000
   8.000   1.0154   0.02920   0.02176  -0.0356   0.0301   1.0000
   8.250   1.0356   0.03198   0.02488  -0.0343   0.0301   1.0000
   8.500   1.0523   0.03523   0.02855  -0.0327   0.0305   1.0000
   8.750   1.0660   0.03828   0.03202  -0.0308   0.0302   1.0000
   9.000   1.0762   0.04157   0.03573  -0.0288   0.0298   1.0000
   9.250   1.0798   0.04608   0.04067  -0.0265   0.0307   1.0000
   9.500   1.0778   0.05150   0.04642  -0.0244   0.0320   1.0000
  12.250   0.7363   0.13423   0.13123  -0.0457   0.0668   1.0000
  12.500   0.7093   0.14056   0.13753  -0.0524   0.0649   1.0000
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