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S2062 8% (s2062-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S2062 8% (s2062-il)
Reynolds number: 1,000,000
Max Cl/Cd: 99.65 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2062-il-1000000.txt
Download as CSV file: xf-s2062-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.6547   0.02572   0.02262  -0.0440   0.9997   0.0070
  -7.500  -0.6280   0.02201   0.01845  -0.0460   0.9977   0.0071
  -7.250  -0.5983   0.01954   0.01563  -0.0476   0.9960   0.0070
  -7.000  -0.5677   0.01734   0.01313  -0.0492   0.9946   0.0071
  -6.750  -0.5384   0.01571   0.01126  -0.0501   0.9925   0.0071
  -6.500  -0.5080   0.01436   0.00972  -0.0510   0.9902   0.0071
  -6.250  -0.4768   0.01304   0.00825  -0.0521   0.9882   0.0073
  -6.000  -0.4442   0.01219   0.00731  -0.0535   0.9865   0.0077
  -5.750  -0.4109   0.01128   0.00627  -0.0548   0.9851   0.0078
  -5.500  -0.3768   0.01046   0.00534  -0.0563   0.9839   0.0079
  -5.250  -0.3450   0.00983   0.00462  -0.0573   0.9817   0.0082
  -5.000  -0.3139   0.00930   0.00402  -0.0580   0.9785   0.0087
  -4.750  -0.2810   0.00886   0.00352  -0.0591   0.9759   0.0097
  -4.500  -0.2480   0.00837   0.00294  -0.0602   0.9733   0.0114
  -4.250  -0.2150   0.00802   0.00256  -0.0612   0.9707   0.0144
  -4.000  -0.1880   0.00748   0.00221  -0.0611   0.9646   0.0482
  -3.750  -0.1589   0.00722   0.00201  -0.0614   0.9593   0.0667
  -3.500  -0.1304   0.00697   0.00183  -0.0615   0.9536   0.0872
  -3.250  -0.1036   0.00673   0.00166  -0.0613   0.9461   0.1122
  -3.000  -0.0763   0.00649   0.00152  -0.0611   0.9390   0.1447
  -2.750  -0.0498   0.00622   0.00138  -0.0609   0.9306   0.1880
  -2.500  -0.0232   0.00599   0.00126  -0.0606   0.9216   0.2301
  -2.250   0.0036   0.00579   0.00115  -0.0603   0.9129   0.2715
  -2.000   0.0302   0.00555   0.00106  -0.0601   0.9031   0.3250
  -1.750   0.0568   0.00533   0.00098  -0.0598   0.8932   0.3850
  -1.500   0.0833   0.00508   0.00092  -0.0596   0.8829   0.4562
  -1.250   0.1097   0.00486   0.00086  -0.0593   0.8717   0.5250
  -1.000   0.1358   0.00459   0.00083  -0.0589   0.8596   0.6115
  -0.750   0.1618   0.00438   0.00083  -0.0584   0.8473   0.6934
  -0.500   0.1880   0.00427   0.00083  -0.0579   0.8343   0.7480
  -0.250   0.2144   0.00422   0.00084  -0.0574   0.8204   0.7866
   0.000   0.2406   0.00420   0.00085  -0.0569   0.8054   0.8170
   0.250   0.2668   0.00419   0.00086  -0.0563   0.7889   0.8429
   0.500   0.2925   0.00420   0.00087  -0.0556   0.7710   0.8672
   0.750   0.3180   0.00423   0.00089  -0.0549   0.7504   0.8888
   1.000   0.3427   0.00427   0.00091  -0.0540   0.7281   0.9106
   1.250   0.3668   0.00434   0.00094  -0.0530   0.7029   0.9323
   1.750   0.4235   0.00455   0.00100  -0.0529   0.6423   0.9768
   2.000   0.4589   0.00472   0.00104  -0.0546   0.6060   0.9923
   2.250   0.4893   0.00492   0.00111  -0.0552   0.5691   1.0000
   2.500   0.5142   0.00516   0.00119  -0.0547   0.5302   1.0000
   2.750   0.5379   0.00555   0.00131  -0.0540   0.4638   1.0000
   3.000   0.5624   0.00593   0.00144  -0.0534   0.4053   1.0000
   3.250   0.5872   0.00630   0.00160  -0.0529   0.3514   1.0000
   3.500   0.6119   0.00670   0.00178  -0.0525   0.2970   1.0000
   3.750   0.6370   0.00708   0.00196  -0.0521   0.2514   1.0000
   4.000   0.6618   0.00751   0.00217  -0.0517   0.2010   1.0000
   4.250   0.6865   0.00795   0.00242  -0.0513   0.1554   1.0000
   4.500   0.7111   0.00843   0.00269  -0.0508   0.1111   1.0000
   4.750   0.7343   0.00911   0.00307  -0.0502   0.0537   1.0000
   5.000   0.7579   0.00977   0.00353  -0.0495   0.0189   1.0000
   5.250   0.7836   0.01013   0.00390  -0.0491   0.0159   1.0000
   5.500   0.8090   0.01055   0.00439  -0.0486   0.0144   1.0000
   5.750   0.8342   0.01098   0.00489  -0.0481   0.0138   1.0000
   6.000   0.8594   0.01138   0.00534  -0.0476   0.0135   1.0000
   6.250   0.8843   0.01183   0.00584  -0.0471   0.0130   1.0000
   6.500   0.9087   0.01235   0.00644  -0.0465   0.0124   1.0000
   6.750   0.9328   0.01287   0.00702  -0.0459   0.0118   1.0000
   7.000   0.9564   0.01347   0.00766  -0.0452   0.0111   1.0000
   7.250   0.9792   0.01416   0.00842  -0.0444   0.0107   1.0000
   7.500   1.0011   0.01498   0.00931  -0.0435   0.0103   1.0000
   7.750   1.0214   0.01606   0.01048  -0.0423   0.0100   1.0000
   8.000   1.0387   0.01778   0.01234  -0.0407   0.0095   1.0000
   8.250   1.0570   0.01958   0.01431  -0.0393   0.0091   1.0000
   8.500   1.0816   0.01973   0.01452  -0.0389   0.0088   1.0000
   8.750   1.1034   0.02056   0.01544  -0.0381   0.0084   1.0000
   9.000   1.1240   0.02158   0.01658  -0.0371   0.0080   1.0000
   9.250   1.1432   0.02285   0.01799  -0.0359   0.0077   1.0000
   9.500   1.1620   0.02403   0.01929  -0.0348   0.0074   1.0000
   9.750   1.1800   0.02520   0.02059  -0.0337   0.0071   1.0000
  10.000   1.1969   0.02638   0.02190  -0.0324   0.0069   1.0000
  10.250   1.2124   0.02762   0.02324  -0.0310   0.0066   1.0000
  10.500   1.2252   0.02913   0.02486  -0.0295   0.0064   1.0000
  10.750   1.2205   0.03336   0.02943  -0.0262   0.0061   1.0000
  11.000   1.2052   0.03771   0.03419  -0.0218   0.0059   1.0000
  11.250   1.2134   0.03791   0.03449  -0.0193   0.0058   1.0000
  11.500   1.2152   0.03903   0.03572  -0.0166   0.0056   1.0000
  11.750   1.2029   0.04180   0.03870  -0.0135   0.0056   1.0000
  12.000   1.2058   0.04312   0.04013  -0.0120   0.0053   1.0000
  12.250   1.1919   0.04655   0.04376  -0.0106   0.0052   1.0000
  12.500   1.1816   0.04993   0.04730  -0.0102   0.0051   1.0000
  12.750   1.1582   0.05563   0.05321  -0.0115   0.0051   1.0000
  13.000   1.1396   0.06154   0.05929  -0.0143   0.0051   1.0000
  13.250   1.1142   0.06979   0.06773  -0.0194   0.0052   1.0000
  13.500   1.0873   0.07977   0.07787  -0.0264   0.0054   1.0000
  13.750   1.0666   0.08986   0.08810  -0.0335   0.0053   1.0000
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