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AUGUST 160 (august160-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AUGUST 160 (august160-il)
Reynolds number: 50,000
Max Cl/Cd: 17.34 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-august160-il-50000-n5.txt
Download as CSV file: xf-august160-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AUGUST 160                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1779   0.11340   0.10669  -0.0349   0.6978   0.1201
  -9.750  -0.1806   0.11096   0.10417  -0.0374   0.6833   0.1232
  -9.500  -0.1868   0.10820   0.10142  -0.0404   0.6708   0.1241
  -9.000  -0.1692   0.09560   0.08857  -0.0454   0.6499   0.0645
  -8.750  -0.1770   0.09032   0.08325  -0.0496   0.6438   0.0587
  -8.500  -0.1711   0.08711   0.08003  -0.0507   0.6320   0.0579
  -8.250  -0.1690   0.08357   0.07643  -0.0525   0.6235   0.0568
  -7.750  -0.1980   0.07326   0.06606  -0.0592   0.6124   0.0522
  -7.500  -0.1973   0.07015   0.06283  -0.0594   0.6052   0.0519
  -7.250  -0.1996   0.06660   0.05918  -0.0598   0.5976   0.0519
  -7.000  -0.1975   0.06349   0.05591  -0.0596   0.5903   0.0516
  -6.750  -0.1951   0.06029   0.05247  -0.0592   0.5840   0.0514
  -6.500  -0.1912   0.05708   0.04904  -0.0586   0.5765   0.0514
  -6.250  -0.1839   0.05416   0.04583  -0.0576   0.5699   0.0511
  -6.000  -0.1746   0.05134   0.04267  -0.0565   0.5637   0.0508
  -5.750  -0.1633   0.04865   0.03967  -0.0553   0.5563   0.0505
  -5.500  -0.1497   0.04616   0.03679  -0.0540   0.5499   0.0502
  -5.250  -0.1341   0.04378   0.03397  -0.0526   0.5442   0.0502
  -5.000  -0.1163   0.04167   0.03147  -0.0513   0.5371   0.0503
  -4.750  -0.0963   0.03966   0.02900  -0.0501   0.5310   0.0507
  -4.500  -0.0740   0.03794   0.02681  -0.0490   0.5255   0.0512
  -4.250  -0.0506   0.03644   0.02495  -0.0480   0.5184   0.0521
  -4.000  -0.0264   0.03534   0.02371  -0.0473   0.5123   0.0543
  -3.750  -0.0004   0.03430   0.02235  -0.0466   0.5075   0.0569
  -3.500   0.0254   0.03342   0.02132  -0.0461   0.5008   0.0598
  -3.250   0.0522   0.03261   0.02043  -0.0456   0.4950   0.0626
  -3.000   0.0815   0.03179   0.01932  -0.0452   0.4903   0.0662
  -2.750   0.1083   0.03126   0.01877  -0.0449   0.4851   0.0713
  -2.500   0.1337   0.03089   0.01839  -0.0445   0.4793   0.0794
  -2.250   0.1593   0.03045   0.01785  -0.0438   0.4746   0.0930
  -2.000   0.1838   0.02977   0.01727  -0.0432   0.4710   0.1216
  -1.750   0.2023   0.02869   0.01695  -0.0420   0.4675   0.2370
  -1.500   0.3825   0.02728   0.01731  -0.0658   0.4565   0.9993
  -1.250   0.4033   0.02752   0.01721  -0.0648   0.4531   1.0000
  -1.000   0.4235   0.02775   0.01710  -0.0636   0.4503   1.0000
  -0.750   0.4400   0.02840   0.01767  -0.0624   0.4460   1.0000
  -0.500   0.4571   0.02902   0.01817  -0.0612   0.4422   1.0000
  -0.250   0.4750   0.02959   0.01858  -0.0599   0.4389   1.0000
   0.000   0.4935   0.03010   0.01892  -0.0587   0.4361   1.0000
   0.250   0.5127   0.03059   0.01921  -0.0574   0.4338   1.0000
   0.500   0.5328   0.03103   0.01944  -0.0562   0.4317   1.0000
   0.750   0.5466   0.03205   0.02043  -0.0547   0.4285   1.0000
   1.000   0.5584   0.03321   0.02161  -0.0531   0.4248   1.0000
   1.250   0.5719   0.03418   0.02252  -0.0514   0.4214   1.0000
   1.500   0.5871   0.03500   0.02326  -0.0499   0.4185   1.0000
   1.750   0.6039   0.03570   0.02384  -0.0484   0.4161   1.0000
   2.000   0.6220   0.03634   0.02433  -0.0471   0.4141   1.0000
   2.250   0.6411   0.03697   0.02481  -0.0458   0.4125   1.0000
   2.500   0.6346   0.03958   0.02762  -0.0431   0.4089   1.0000
   2.750   0.6274   0.04220   0.03035  -0.0404   0.4055   1.0000
   3.000   0.6238   0.04449   0.03268  -0.0379   0.4023   1.0000
   3.250   0.6266   0.04626   0.03441  -0.0359   0.3997   1.0000
   3.500   0.6373   0.04746   0.03554  -0.0342   0.3975   1.0000
   3.750   0.6540   0.04827   0.03623  -0.0328   0.3958   1.0000
   4.000   0.6734   0.04893   0.03678  -0.0317   0.3943   1.0000
   4.500   0.5276   0.06518   0.05341  -0.0262   0.3812   1.0000
   4.750   0.5402   0.06662   0.05476  -0.0254   0.3791   1.0000
   5.000   0.5565   0.06782   0.05587  -0.0246   0.3775   1.0000
   5.250   0.5737   0.06905   0.05701  -0.0238   0.3762   1.0000
   5.500   0.5251   0.07619   0.06424  -0.0244   0.3712   1.0000
   5.750   0.5210   0.07925   0.06728  -0.0243   0.3679   1.0000
   6.000   0.5256   0.08162   0.06961  -0.0240   0.3654   1.0000
   6.250   0.5335   0.08380   0.07175  -0.0238   0.3634   1.0000
   6.500   0.5434   0.08587   0.07379  -0.0235   0.3619   1.0000
   6.750   0.5553   0.08785   0.07572  -0.0233   0.3605   1.0000
   7.000   0.5737   0.08930   0.07712  -0.0228   0.3590   1.0000
   7.250   0.5648   0.09295   0.08078  -0.0232   0.3561   1.0000
   7.500   0.5569   0.09640   0.08426  -0.0236   0.3529   1.0000
   7.750   0.5585   0.09921   0.08708  -0.0238   0.3507   1.0000
   8.000   0.5630   0.10187   0.08974  -0.0240   0.3491   1.0000
   8.250   0.5702   0.10427   0.09214  -0.0241   0.3472   1.0000
   8.500   0.5823   0.10629   0.09415  -0.0240   0.3451   1.0000
   8.750   0.6004   0.10790   0.09573  -0.0237   0.3429   1.0000
   9.000   0.6225   0.10936   0.09717  -0.0234   0.3413   1.0000
   9.250   0.6037   0.11348   0.10135  -0.0243   0.3377   1.0000
   9.500   0.6027   0.11623   0.10413  -0.0247   0.3341   1.0000
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