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S2060 8% (s2060-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S2060 8% (s2060-il)
Reynolds number: 1,000,000
Max Cl/Cd: 101.46 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2060-il-1000000.txt
Download as CSV file: xf-s2060-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.7664   0.03351   0.03118  -0.0557   1.0000   0.0062
  -9.500  -0.7688   0.02959   0.02692  -0.0545   1.0000   0.0062
  -9.250  -0.7647   0.02656   0.02358  -0.0529   1.0000   0.0062
  -9.000  -0.7569   0.02402   0.02074  -0.0512   1.0000   0.0063
  -8.750  -0.7460   0.02184   0.01829  -0.0494   1.0000   0.0063
  -8.500  -0.7329   0.01997   0.01618  -0.0477   1.0000   0.0064
  -8.250  -0.7179   0.01837   0.01435  -0.0461   1.0000   0.0064
  -8.000  -0.6887   0.01696   0.01275  -0.0473   0.9988   0.0066
  -7.750  -0.6575   0.01578   0.01140  -0.0487   0.9973   0.0068
  -7.500  -0.6253   0.01489   0.01039  -0.0502   0.9959   0.0071
  -7.250  -0.5930   0.01378   0.00911  -0.0516   0.9947   0.0073
  -7.000  -0.5623   0.01281   0.00798  -0.0525   0.9928   0.0075
  -6.750  -0.5312   0.01198   0.00703  -0.0535   0.9907   0.0078
  -6.500  -0.4989   0.01131   0.00625  -0.0546   0.9887   0.0083
  -6.250  -0.4655   0.01084   0.00570  -0.0559   0.9871   0.0087
  -6.000  -0.4323   0.00994   0.00468  -0.0573   0.9856   0.0100
  -5.750  -0.3979   0.00951   0.00421  -0.0589   0.9844   0.0112
  -5.500  -0.3628   0.00908   0.00371  -0.0605   0.9835   0.0134
  -5.250  -0.3339   0.00862   0.00332  -0.0608   0.9796   0.0221
  -5.000  -0.3009   0.00836   0.00311  -0.0620   0.9772   0.0309
  -4.750  -0.2674   0.00813   0.00287  -0.0632   0.9748   0.0360
  -4.500  -0.2340   0.00790   0.00265  -0.0645   0.9725   0.0416
  -4.250  -0.2019   0.00768   0.00242  -0.0654   0.9696   0.0470
  -4.000  -0.1744   0.00748   0.00225  -0.0652   0.9634   0.0543
  -3.750  -0.1448   0.00724   0.00205  -0.0656   0.9586   0.0657
  -3.500  -0.1168   0.00703   0.00186  -0.0655   0.9523   0.0781
  -3.250  -0.0893   0.00682   0.00168  -0.0654   0.9451   0.0935
  -3.000  -0.0622   0.00661   0.00154  -0.0651   0.9375   0.1162
  -2.750  -0.0351   0.00639   0.00140  -0.0649   0.9296   0.1445
  -2.500  -0.0083   0.00619   0.00128  -0.0646   0.9206   0.1780
  -2.250   0.0186   0.00597   0.00117  -0.0644   0.9120   0.2197
  -2.000   0.0452   0.00572   0.00107  -0.0642   0.9020   0.2757
  -1.750   0.0719   0.00549   0.00099  -0.0639   0.8918   0.3352
  -1.500   0.0984   0.00522   0.00092  -0.0637   0.8814   0.4102
  -1.250   0.1248   0.00495   0.00087  -0.0634   0.8704   0.4937
  -1.000   0.1511   0.00469   0.00084  -0.0631   0.8586   0.5843
  -0.750   0.1776   0.00453   0.00083  -0.0627   0.8462   0.6498
  -0.250   0.2309   0.00437   0.00083  -0.0619   0.8192   0.7372
   0.000   0.2574   0.00432   0.00084  -0.0614   0.8039   0.7724
   0.250   0.2836   0.00430   0.00085  -0.0609   0.7871   0.8046
   0.500   0.3094   0.00428   0.00087  -0.0602   0.7685   0.8360
   0.750   0.3347   0.00428   0.00090  -0.0595   0.7476   0.8676
   1.000   0.3591   0.00430   0.00093  -0.0585   0.7250   0.8995
   1.250   0.3825   0.00434   0.00096  -0.0572   0.6997   0.9326
   1.500   0.4105   0.00442   0.00098  -0.0570   0.6710   0.9660
   1.750   0.4479   0.00456   0.00100  -0.0591   0.6355   0.9932
   2.000   0.4765   0.00476   0.00106  -0.0593   0.5998   1.0000
   2.250   0.5022   0.00495   0.00113  -0.0588   0.5667   1.0000
   2.500   0.5276   0.00520   0.00121  -0.0584   0.5270   1.0000
   2.750   0.5521   0.00556   0.00133  -0.0578   0.4675   1.0000
   3.000   0.5763   0.00599   0.00148  -0.0572   0.4003   1.0000
   3.250   0.6016   0.00633   0.00163  -0.0568   0.3521   1.0000
   3.500   0.6265   0.00671   0.00180  -0.0563   0.3015   1.0000
   3.750   0.6515   0.00711   0.00199  -0.0559   0.2520   1.0000
   4.000   0.6767   0.00750   0.00220  -0.0555   0.2090   1.0000
   4.250   0.7017   0.00791   0.00242  -0.0551   0.1669   1.0000
   4.500   0.7259   0.00843   0.00270  -0.0546   0.1176   1.0000
   4.750   0.7499   0.00899   0.00303  -0.0540   0.0714   1.0000
   5.000   0.7727   0.00976   0.00351  -0.0533   0.0222   1.0000
   5.250   0.7982   0.01016   0.00390  -0.0528   0.0169   1.0000
   5.500   0.8241   0.01047   0.00424  -0.0524   0.0156   1.0000
   5.750   0.8495   0.01084   0.00465  -0.0520   0.0145   1.0000
   6.000   0.8747   0.01125   0.00510  -0.0515   0.0137   1.0000
   6.250   0.8992   0.01176   0.00567  -0.0509   0.0130   1.0000
   6.500   0.9227   0.01243   0.00642  -0.0501   0.0124   1.0000
   6.750   0.9434   0.01347   0.00759  -0.0489   0.0119   1.0000
   7.000   0.9679   0.01393   0.00810  -0.0483   0.0117   1.0000
   7.250   0.9919   0.01444   0.00867  -0.0477   0.0113   1.0000
   7.500   1.0153   0.01502   0.00931  -0.0470   0.0109   1.0000
   7.750   1.0376   0.01578   0.01014  -0.0461   0.0105   1.0000
   8.000   1.0593   0.01662   0.01105  -0.0451   0.0101   1.0000
   8.250   1.0807   0.01751   0.01202  -0.0442   0.0099   1.0000
   8.500   1.1019   0.01840   0.01299  -0.0432   0.0096   1.0000
   8.750   1.1227   0.01936   0.01405  -0.0422   0.0093   1.0000
   9.000   1.1429   0.02038   0.01514  -0.0412   0.0090   1.0000
   9.250   1.1614   0.02166   0.01650  -0.0401   0.0086   1.0000
   9.750   1.1911   0.02575   0.02099  -0.0369   0.0078   1.0000
  10.000   1.2083   0.02694   0.02234  -0.0355   0.0077   1.0000
  10.250   1.2238   0.02830   0.02387  -0.0340   0.0074   1.0000
  10.500   1.2362   0.03001   0.02578  -0.0322   0.0072   1.0000
  10.750   1.2450   0.03203   0.02802  -0.0300   0.0070   1.0000
  11.000   1.2505   0.03415   0.03035  -0.0276   0.0069   1.0000
  11.250   1.2550   0.03575   0.03211  -0.0251   0.0066   1.0000
  11.500   1.2484   0.03793   0.03449  -0.0212   0.0066   1.0000
  11.750   1.2445   0.03974   0.03643  -0.0182   0.0064   1.0000
  12.000   1.2289   0.04298   0.03990  -0.0151   0.0064   1.0000
  12.250   1.2146   0.04632   0.04344  -0.0133   0.0064   1.0000
  12.500   1.2001   0.05007   0.04736  -0.0126   0.0064   1.0000
  12.750   1.1976   0.05262   0.04998  -0.0128   0.0062   1.0000
  13.000   1.1942   0.05561   0.05305  -0.0135   0.0061   1.0000
  13.250   1.1560   0.06472   0.06246  -0.0177   0.0062   1.0000
  13.500   1.1071   0.07825   0.07630  -0.0265   0.0065   1.0000
  13.750   1.0912   0.08659   0.08477  -0.0326   0.0064   1.0000
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