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S2062 8% (s2062-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S2062 8% (s2062-il)
Reynolds number: 1,000,000
Max Cl/Cd: 78.87 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2062-il-1000000-n5.txt
Download as CSV file: xf-s2062-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5328   0.10876   0.10704  -0.0123   1.0000   0.0028
 -10.750  -0.5405   0.10215   0.10046  -0.0148   1.0000   0.0026
 -10.250  -0.8084   0.03443   0.03221  -0.0537   1.0000   0.0023
 -10.000  -0.8098   0.03064   0.02813  -0.0530   1.0000   0.0023
  -9.750  -0.8013   0.02840   0.02569  -0.0520   1.0000   0.0024
  -9.500  -0.7930   0.02600   0.02304  -0.0506   1.0000   0.0024
  -9.250  -0.7807   0.02427   0.02111  -0.0491   1.0000   0.0025
  -9.000  -0.7587   0.02244   0.01906  -0.0496   0.9989   0.0026
  -8.750  -0.7312   0.02097   0.01740  -0.0508   0.9970   0.0027
  -8.500  -0.7030   0.01955   0.01579  -0.0521   0.9952   0.0028
  -8.250  -0.6754   0.01819   0.01422  -0.0530   0.9932   0.0029
  -8.000  -0.6477   0.01709   0.01295  -0.0537   0.9908   0.0031
  -7.750  -0.6191   0.01586   0.01152  -0.0545   0.9885   0.0032
  -7.500  -0.5892   0.01485   0.01034  -0.0555   0.9865   0.0033
  -7.250  -0.5585   0.01396   0.00931  -0.0565   0.9849   0.0034
  -7.000  -0.5272   0.01309   0.00831  -0.0576   0.9834   0.0036
  -6.750  -0.4999   0.01245   0.00756  -0.0578   0.9794   0.0037
  -6.500  -0.4711   0.01180   0.00681  -0.0582   0.9755   0.0038
  -6.250  -0.4408   0.01128   0.00620  -0.0589   0.9722   0.0039
  -6.000  -0.4105   0.01095   0.00582  -0.0596   0.9688   0.0040
  -5.750  -0.3844   0.01004   0.00476  -0.0594   0.9624   0.0044
  -5.500  -0.3554   0.00952   0.00416  -0.0598   0.9574   0.0047
  -5.250  -0.3279   0.00910   0.00368  -0.0597   0.9508   0.0050
  -5.000  -0.2999   0.00876   0.00328  -0.0597   0.9440   0.0055
  -4.750  -0.2726   0.00848   0.00293  -0.0596   0.9364   0.0060
  -4.250  -0.2180   0.00805   0.00237  -0.0592   0.9192   0.0070
  -4.000  -0.1909   0.00783   0.00211  -0.0590   0.9100   0.0091
  -3.500  -0.1374   0.00727   0.00165  -0.0585   0.8903   0.0419
  -3.250  -0.1103   0.00711   0.00150  -0.0584   0.8806   0.0550
  -3.000  -0.0834   0.00692   0.00136  -0.0582   0.8703   0.0769
  -2.750  -0.0564   0.00678   0.00123  -0.0580   0.8589   0.0955
  -2.500  -0.0294   0.00660   0.00111  -0.0578   0.8466   0.1237
  -2.250  -0.0024   0.00643   0.00101  -0.0577   0.8340   0.1567
  -2.000   0.0248   0.00632   0.00092  -0.0575   0.8212   0.1811
  -1.750   0.0518   0.00618   0.00085  -0.0573   0.8073   0.2144
  -1.500   0.0789   0.00609   0.00078  -0.0572   0.7914   0.2441
  -1.250   0.1057   0.00598   0.00072  -0.0570   0.7735   0.2845
  -1.000   0.1326   0.00588   0.00068  -0.0568   0.7539   0.3237
  -0.500   0.1859   0.00570   0.00062  -0.0564   0.7098   0.4219
  -0.250   0.2124   0.00561   0.00061  -0.0562   0.6863   0.4784
   0.000   0.2388   0.00552   0.00062  -0.0559   0.6613   0.5390
   0.250   0.2650   0.00544   0.00064  -0.0557   0.6348   0.6052
   0.500   0.2911   0.00537   0.00068  -0.0553   0.6076   0.6744
   0.750   0.3171   0.00538   0.00074  -0.0549   0.5789   0.7256
   1.000   0.3433   0.00546   0.00080  -0.0545   0.5486   0.7613
   1.250   0.3693   0.00556   0.00088  -0.0541   0.5162   0.7902
   1.500   0.3951   0.00569   0.00096  -0.0537   0.4819   0.8170
   1.750   0.4207   0.00582   0.00105  -0.0532   0.4488   0.8420
   2.000   0.4461   0.00598   0.00115  -0.0527   0.4132   0.8634
   2.250   0.4712   0.00614   0.00125  -0.0520   0.3822   0.8858
   2.500   0.4953   0.00628   0.00136  -0.0512   0.3520   0.9123
   3.000   0.5445   0.00723   0.00172  -0.0501   0.1947   0.9731
   3.250   0.5771   0.00759   0.00190  -0.0515   0.1509   1.0000
   3.500   0.6027   0.00793   0.00209  -0.0511   0.1186   1.0000
   3.750   0.6282   0.00827   0.00229  -0.0508   0.0876   1.0000
   4.000   0.6536   0.00865   0.00254  -0.0505   0.0586   1.0000
   4.250   0.6787   0.00907   0.00282  -0.0501   0.0292   1.0000
   4.500   0.7042   0.00946   0.00311  -0.0497   0.0142   1.0000
   4.750   0.7305   0.00972   0.00336  -0.0494   0.0119   1.0000
   5.000   0.7567   0.00999   0.00367  -0.0491   0.0107   1.0000
   5.250   0.7829   0.01026   0.00397  -0.0488   0.0102   1.0000
   5.500   0.8089   0.01053   0.00428  -0.0485   0.0100   1.0000
   5.750   0.8348   0.01084   0.00462  -0.0482   0.0098   1.0000
   6.000   0.8604   0.01117   0.00498  -0.0478   0.0095   1.0000
   6.250   0.8859   0.01152   0.00537  -0.0475   0.0093   1.0000
   6.500   0.9110   0.01191   0.00581  -0.0470   0.0090   1.0000
   6.750   0.9359   0.01232   0.00629  -0.0466   0.0088   1.0000
   7.000   0.9606   0.01276   0.00678  -0.0461   0.0085   1.0000
   7.250   0.9849   0.01323   0.00730  -0.0456   0.0081   1.0000
   7.500   1.0089   0.01373   0.00786  -0.0450   0.0079   1.0000
   7.750   1.0329   0.01421   0.00838  -0.0445   0.0075   1.0000
   8.000   1.0561   0.01477   0.00899  -0.0438   0.0071   1.0000
   8.250   1.0777   0.01556   0.00986  -0.0429   0.0068   1.0000
   8.500   1.0960   0.01680   0.01125  -0.0416   0.0064   1.0000
   8.750   1.1154   0.01788   0.01244  -0.0404   0.0063   1.0000
   9.000   1.1383   0.01839   0.01302  -0.0397   0.0062   1.0000
   9.250   1.1610   0.01890   0.01359  -0.0391   0.0060   1.0000
   9.500   1.1834   0.01942   0.01418  -0.0384   0.0058   1.0000
   9.750   1.2045   0.02009   0.01494  -0.0376   0.0057   1.0000
  10.000   1.2247   0.02085   0.01581  -0.0366   0.0054   1.0000
  10.250   1.2440   0.02168   0.01673  -0.0356   0.0052   1.0000
  10.500   1.2629   0.02248   0.01764  -0.0345   0.0050   1.0000
  10.750   1.2819   0.02321   0.01845  -0.0335   0.0048   1.0000
  11.000   1.3013   0.02381   0.01912  -0.0325   0.0046   1.0000
  11.250   1.3214   0.02425   0.01960  -0.0317   0.0044   1.0000
  11.500   1.3405   0.02476   0.02015  -0.0307   0.0042   1.0000
  11.750   1.3591   0.02528   0.02070  -0.0297   0.0040   1.0000
  12.000   1.3738   0.02612   0.02161  -0.0282   0.0039   1.0000
  12.250   1.3788   0.02747   0.02311  -0.0254   0.0037   1.0000
  12.500   1.3845   0.02861   0.02436  -0.0226   0.0036   1.0000
  12.750   1.3901   0.02977   0.02565  -0.0201   0.0036   1.0000
  13.000   1.3955   0.03100   0.02699  -0.0179   0.0035   1.0000
  13.250   1.3989   0.03243   0.02855  -0.0157   0.0034   1.0000
  13.500   1.3992   0.03423   0.03048  -0.0137   0.0034   1.0000
  13.750   1.4015   0.03596   0.03233  -0.0122   0.0033   1.0000
  14.000   1.4010   0.03808   0.03458  -0.0109   0.0032   1.0000
  14.250   1.3986   0.04057   0.03720  -0.0101   0.0031   1.0000
  14.500   1.3900   0.04399   0.04078  -0.0098   0.0030   1.0000
  14.750   1.3889   0.04684   0.04373  -0.0101   0.0030   1.0000
  15.000   1.3792   0.05111   0.04815  -0.0112   0.0029   1.0000
  15.250   1.3627   0.05687   0.05410  -0.0137   0.0029   1.0000
  15.500   1.3486   0.06294   0.06032  -0.0169   0.0029   1.0000
  15.750   1.3317   0.07009   0.06762  -0.0211   0.0028   1.0000
  16.000   1.3110   0.07858   0.07627  -0.0264   0.0028   1.0000
  16.250   1.2634   0.09341   0.09135  -0.0356   0.0030   1.0000
  16.500   1.2179   0.10864   0.10677  -0.0447   0.0030   1.0000
  16.750   1.1585   0.12810   0.12642  -0.0562   0.0033   1.0000
  17.000   1.0945   0.15048   0.14895  -0.0691   0.0034   1.0000
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