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S6062 8% (s6062-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S6062 8% (s6062-il)
Reynolds number: 1,000,000
Max Cl/Cd: 73.17 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s6062-il-1000000-n5.txt
Download as CSV file: xf-s6062-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6062 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5553   0.08057   0.07900  -0.0123   1.0000   0.0035
  -8.750  -0.5627   0.07524   0.07370  -0.0157   1.0000   0.0034
  -8.500  -0.5741   0.06955   0.06805  -0.0199   1.0000   0.0033
  -8.250  -0.5856   0.06195   0.06045  -0.0279   1.0000   0.0034
  -8.000  -0.5912   0.05320   0.05159  -0.0340   1.0000   0.0033
  -7.750  -0.5964   0.04335   0.04149  -0.0375   1.0000   0.0033
  -7.500  -0.6037   0.03179   0.02940  -0.0381   1.0000   0.0033
  -7.250  -0.5862   0.02585   0.02293  -0.0396   0.9859   0.0034
  -7.000  -0.5611   0.02251   0.01917  -0.0408   0.9730   0.0035
  -6.750  -0.5355   0.02080   0.01718  -0.0411   0.9605   0.0036
  -6.500  -0.5122   0.01940   0.01551  -0.0407   0.9479   0.0036
  -6.250  -0.4897   0.01800   0.01384  -0.0400   0.9360   0.0037
  -6.000  -0.4680   0.01617   0.01171  -0.0392   0.9249   0.0037
  -5.750  -0.4447   0.01490   0.01021  -0.0384   0.9145   0.0037
  -5.500  -0.4207   0.01361   0.00870  -0.0377   0.9041   0.0037
  -5.250  -0.3962   0.01247   0.00738  -0.0371   0.8943   0.0037
  -5.000  -0.3718   0.01133   0.00606  -0.0365   0.8846   0.0038
  -4.750  -0.3471   0.01034   0.00488  -0.0359   0.8743   0.0040
  -4.500  -0.3212   0.00972   0.00416  -0.0356   0.8641   0.0042
  -4.250  -0.2948   0.00930   0.00366  -0.0353   0.8541   0.0045
  -4.000  -0.2681   0.00896   0.00324  -0.0350   0.8438   0.0048
  -3.750  -0.2411   0.00867   0.00288  -0.0348   0.8331   0.0053
  -3.500  -0.2139   0.00841   0.00253  -0.0346   0.8225   0.0057
  -3.250  -0.1866   0.00819   0.00223  -0.0345   0.8118   0.0060
  -3.000  -0.1592   0.00801   0.00198  -0.0343   0.8005   0.0064
  -2.750  -0.1318   0.00785   0.00174  -0.0342   0.7889   0.0071
  -2.500  -0.1041   0.00768   0.00148  -0.0341   0.7767   0.0082
  -2.250  -0.0765   0.00755   0.00129  -0.0339   0.7642   0.0107
  -2.000  -0.0492   0.00729   0.00112  -0.0339   0.7514   0.0406
  -1.750  -0.0219   0.00707   0.00099  -0.0338   0.7381   0.0803
  -1.500   0.0049   0.00672   0.00087  -0.0338   0.7243   0.1583
  -1.250   0.0320   0.00646   0.00078  -0.0338   0.7099   0.2285
  -1.000   0.0585   0.00606   0.00071  -0.0338   0.6950   0.3429
  -0.750   0.0853   0.00579   0.00066  -0.0337   0.6793   0.4318
  -0.500   0.1125   0.00565   0.00062  -0.0337   0.6628   0.4892
  -0.250   0.1395   0.00548   0.00060  -0.0336   0.6447   0.5591
   0.000   0.1663   0.00533   0.00060  -0.0335   0.6255   0.6301
   0.250   0.1930   0.00523   0.00061  -0.0333   0.6063   0.6899
   0.500   0.2198   0.00517   0.00063  -0.0330   0.5867   0.7391
   0.750   0.2465   0.00515   0.00067  -0.0327   0.5669   0.7808
   1.000   0.2730   0.00516   0.00071  -0.0324   0.5464   0.8166
   1.250   0.2992   0.00519   0.00076  -0.0320   0.5248   0.8487
   1.500   0.3253   0.00524   0.00082  -0.0315   0.5023   0.8761
   1.750   0.3510   0.00531   0.00088  -0.0310   0.4785   0.9012
   2.000   0.3756   0.00549   0.00096  -0.0302   0.4365   0.9280
   2.250   0.4010   0.00586   0.00108  -0.0298   0.3624   0.9556
   2.500   0.4330   0.00619   0.00120  -0.0309   0.3054   0.9761
   2.750   0.4662   0.00665   0.00136  -0.0325   0.2364   0.9915
   3.000   0.4960   0.00705   0.00153  -0.0332   0.1831   1.0000
   3.250   0.5213   0.00744   0.00173  -0.0329   0.1375   1.0000
   3.500   0.5464   0.00790   0.00196  -0.0326   0.0871   1.0000
   3.750   0.5711   0.00844   0.00226  -0.0323   0.0352   1.0000
   4.000   0.5969   0.00882   0.00252  -0.0320   0.0120   1.0000
   4.250   0.6237   0.00901   0.00273  -0.0318   0.0110   1.0000
   4.500   0.6504   0.00921   0.00294  -0.0317   0.0104   1.0000
   4.750   0.6770   0.00944   0.00319  -0.0315   0.0098   1.0000
   5.000   0.7035   0.00969   0.00346  -0.0313   0.0093   1.0000
   5.250   0.7298   0.00998   0.00377  -0.0311   0.0088   1.0000
   5.500   0.7558   0.01033   0.00418  -0.0308   0.0081   1.0000
   5.750   0.7813   0.01078   0.00470  -0.0305   0.0076   1.0000
   6.000   0.8062   0.01133   0.00533  -0.0300   0.0073   1.0000
   6.250   0.8308   0.01190   0.00596  -0.0296   0.0070   1.0000
   6.500   0.8565   0.01224   0.00633  -0.0293   0.0069   1.0000
   6.750   0.8813   0.01273   0.00687  -0.0289   0.0068   1.0000
   7.000   0.9057   0.01326   0.00749  -0.0285   0.0067   1.0000
   7.250   0.9298   0.01384   0.00813  -0.0280   0.0066   1.0000
   7.500   0.9536   0.01445   0.00881  -0.0275   0.0064   1.0000
   7.750   0.9769   0.01510   0.00953  -0.0270   0.0063   1.0000
   8.000   0.9998   0.01581   0.01032  -0.0264   0.0061   1.0000
   8.250   1.0224   0.01655   0.01114  -0.0257   0.0059   1.0000
   8.500   1.0445   0.01735   0.01203  -0.0251   0.0058   1.0000
   8.750   1.0659   0.01824   0.01303  -0.0243   0.0056   1.0000
   9.000   1.0872   0.01911   0.01400  -0.0236   0.0054   1.0000
   9.250   1.1079   0.02004   0.01504  -0.0228   0.0052   1.0000
   9.500   1.1278   0.02106   0.01616  -0.0219   0.0050   1.0000
   9.750   1.1479   0.02191   0.01710  -0.0211   0.0049   1.0000
  10.000   1.1684   0.02260   0.01786  -0.0205   0.0047   1.0000
  10.250   1.1864   0.02362   0.01898  -0.0195   0.0046   1.0000
  10.500   1.2029   0.02477   0.02024  -0.0184   0.0044   1.0000
  10.750   1.2167   0.02616   0.02176  -0.0170   0.0043   1.0000
  11.000   1.2244   0.02824   0.02404  -0.0151   0.0042   1.0000
  11.250   1.2242   0.03104   0.02709  -0.0125   0.0041   1.0000
  11.500   1.2158   0.03369   0.02998  -0.0088   0.0040   1.0000
  11.750   1.2136   0.03544   0.03189  -0.0061   0.0040   1.0000
  12.000   1.2120   0.03729   0.03388  -0.0042   0.0040   1.0000
  12.250   1.2100   0.03936   0.03609  -0.0028   0.0040   1.0000
  12.500   1.2062   0.04184   0.03871  -0.0020   0.0039   1.0000
  12.750   1.1938   0.04566   0.04272  -0.0019   0.0039   1.0000
  13.000   1.1882   0.04903   0.04622  -0.0026   0.0039   1.0000
  13.250   1.1765   0.05364   0.05099  -0.0044   0.0039   1.0000
  13.500   1.1735   0.05743   0.05490  -0.0063   0.0038   1.0000
  13.750   1.1532   0.06455   0.06221  -0.0105   0.0038   1.0000
  14.000   1.1420   0.07078   0.06856  -0.0145   0.0038   1.0000
  14.250   1.1087   0.08222   0.08019  -0.0220   0.0039   1.0000
  14.500   1.0698   0.09624   0.09439  -0.0310   0.0039   1.0000
  14.750   1.0409   0.10887   0.10715  -0.0387   0.0040   1.0000
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