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S6062 8% (s6062-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S6062 8% (s6062-il)
Reynolds number: 50,000
Max Cl/Cd: 34.59 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s6062-il-50000.txt
Download as CSV file: xf-s6062-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4007   0.09865   0.09235  -0.0028   1.0000   0.2438
  -8.500  -0.4035   0.09515   0.08892  -0.0035   1.0000   0.2526
  -8.250  -0.5171   0.10300   0.09647  -0.0003   1.0000   0.2495
  -8.000  -0.4995   0.09830   0.09174   0.0008   1.0000   0.2621
  -7.750  -0.4888   0.09432   0.08778   0.0012   1.0000   0.2736
  -7.500  -0.4840   0.09092   0.08445   0.0013   1.0000   0.2862
  -7.250  -0.4807   0.08768   0.08128   0.0014   1.0000   0.3000
  -7.000  -0.4790   0.08469   0.07837   0.0018   1.0000   0.3159
  -6.750  -0.4934   0.08295   0.07678   0.0016   1.0000   0.3340
  -6.500  -0.4692   0.07846   0.07228   0.0042   1.0000   0.3552
  -5.750  -0.4754   0.05169   0.04427  -0.0367   1.0000   0.1236
  -5.500  -0.4586   0.04641   0.03848  -0.0370   1.0000   0.1095
  -5.250  -0.4416   0.04239   0.03431  -0.0364   1.0000   0.1047
  -5.000  -0.4238   0.03853   0.02992  -0.0359   1.0000   0.1016
  -4.750  -0.4045   0.03542   0.02635  -0.0350   1.0000   0.1020
  -4.500  -0.3835   0.03261   0.02309  -0.0339   1.0000   0.1033
  -4.250  -0.3610   0.02996   0.01998  -0.0327   1.0000   0.1045
  -4.000  -0.3372   0.02758   0.01713  -0.0314   1.0000   0.1076
  -3.750  -0.3138   0.02545   0.01483  -0.0300   1.0000   0.1156
  -3.500  -0.2907   0.02372   0.01293  -0.0286   1.0000   0.1364
  -3.250  -0.2678   0.02163   0.01117  -0.0271   1.0000   0.1849
  -3.000  -0.2504   0.01845   0.00944  -0.0249   1.0000   0.3836
  -2.750  -0.1212   0.01632   0.00846  -0.0338   1.0000   1.0000
  -2.500  -0.1225   0.01602   0.00790  -0.0304   1.0000   1.0000
  -2.250  -0.1201   0.01585   0.00749  -0.0272   1.0000   1.0000
  -2.000  -0.1140   0.01577   0.00715  -0.0243   1.0000   1.0000
  -1.750  -0.1040   0.01577   0.00686  -0.0220   1.0000   1.0000
  -1.500  -0.0908   0.01582   0.00665  -0.0202   1.0000   1.0000
  -1.250  -0.0757   0.01591   0.00649  -0.0187   1.0000   1.0000
  -1.000  -0.0592   0.01604   0.00636  -0.0175   1.0000   1.0000
  -0.750  -0.0420   0.01622   0.00633  -0.0164   1.0000   1.0000
  -0.500  -0.0243   0.01643   0.00636  -0.0155   1.0000   1.0000
  -0.250  -0.0062   0.01668   0.00645  -0.0147   1.0000   1.0000
   0.000   0.0120   0.01697   0.00659  -0.0140   1.0000   1.0000
   0.250   0.0303   0.01730   0.00678  -0.0134   1.0000   1.0000
   0.500   0.0485   0.01768   0.00706  -0.0128   1.0000   1.0000
   0.750   0.0666   0.01811   0.00740  -0.0124   1.0000   1.0000
   1.000   0.0846   0.01858   0.00781  -0.0121   1.0000   1.0000
   1.250   0.1024   0.01911   0.00828  -0.0118   1.0000   1.0000
   1.500   0.1199   0.01969   0.00883  -0.0116   1.0000   1.0000
   1.750   0.1372   0.02034   0.00945  -0.0115   1.0000   1.0000
   2.000   0.1677   0.02127   0.01039  -0.0140   0.9940   1.0000
   2.250   0.2259   0.02257   0.01177  -0.0215   0.9734   1.0000
   2.500   0.2806   0.02370   0.01304  -0.0280   0.9518   1.0000
   2.750   0.3397   0.02473   0.01423  -0.0348   0.9295   1.0000
   3.000   0.3881   0.02548   0.01517  -0.0392   0.9049   1.0000
   3.250   0.4392   0.02608   0.01604  -0.0436   0.8794   1.0000
   3.500   0.4945   0.02640   0.01666  -0.0480   0.8529   1.0000
   3.750   0.5465   0.02642   0.01700  -0.0509   0.8258   1.0000
   4.000   0.5913   0.02621   0.01716  -0.0519   0.7971   1.0000
   4.250   0.6305   0.02578   0.01704  -0.0512   0.7667   1.0000
   4.500   0.6664   0.02509   0.01662  -0.0492   0.7349   1.0000
   4.750   0.6946   0.02450   0.01631  -0.0460   0.6990   1.0000
   5.000   0.7216   0.02376   0.01574  -0.0421   0.6594   1.0000
   5.250   0.7447   0.02322   0.01531  -0.0380   0.6122   1.0000
   5.500   0.7659   0.02282   0.01489  -0.0337   0.5554   1.0000
   5.750   0.7832   0.02264   0.01454  -0.0291   0.4817   1.0000
   6.000   0.7929   0.02306   0.01442  -0.0244   0.3798   1.0000
   6.250   0.7942   0.02489   0.01519  -0.0201   0.2449   1.0000
   6.500   0.8054   0.02837   0.01773  -0.0174   0.1503   1.0000
   6.750   0.8281   0.03100   0.02007  -0.0161   0.1193   1.0000
   7.000   0.8563   0.03383   0.02292  -0.0153   0.1064   1.0000
   7.250   0.8830   0.03679   0.02632  -0.0142   0.1002   1.0000
   7.500   0.9076   0.04003   0.02986  -0.0134   0.0964   1.0000
   7.750   0.9276   0.04386   0.03402  -0.0124   0.0936   1.0000
   8.000   0.9415   0.04747   0.03832  -0.0109   0.0917   1.0000
   8.250   0.9518   0.05148   0.04291  -0.0096   0.0904   1.0000
   8.500   0.9587   0.05594   0.04786  -0.0084   0.0908   1.0000
   8.750   0.9630   0.06078   0.05308  -0.0074   0.0923   1.0000
   9.000   0.9698   0.06592   0.05842  -0.0068   0.0939   1.0000
   9.250   0.9434   0.07120   0.06441  -0.0063   0.0979   1.0000
   9.500   0.9163   0.07707   0.07054  -0.0071   0.1010   1.0000
   9.750   0.8949   0.08239   0.07593  -0.0081   0.1034   1.0000
  10.000   0.8907   0.08794   0.08151  -0.0091   0.1063   1.0000
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