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GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 275 (DAIMLER VI) AIRFOIL (goe275-il)
Reynolds number: 100,000
Max Cl/Cd: 55.86 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe275-il-100000-n5.txt
Download as CSV file: xf-goe275-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 275 (DAIMLER VI) AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3162   0.09409   0.08943  -0.0229   1.0000   0.0355
  -7.250  -0.3231   0.09239   0.08782  -0.0211   1.0000   0.0362
  -7.000  -0.3284   0.09049   0.08600  -0.0200   1.0000   0.0368
  -6.750  -0.3323   0.08846   0.08404  -0.0196   1.0000   0.0380
  -6.500  -0.3352   0.08646   0.08210  -0.0208   1.0000   0.0395
  -6.250  -0.3324   0.08441   0.08006  -0.0255   1.0000   0.0405
  -6.000  -0.3084   0.08093   0.07644  -0.0351   0.9973   0.0409
  -5.750  -0.2975   0.07580   0.07141  -0.0337   0.9940   0.0417
  -5.500  -0.2788   0.07199   0.06760  -0.0349   0.9894   0.0431
  -5.250  -0.2510   0.06805   0.06361  -0.0398   0.9841   0.0454
  -5.000  -0.1887   0.06337   0.05844  -0.0567   0.9763   0.0513
  -4.750  -0.1781   0.05896   0.05422  -0.0554   0.9703   0.0530
  -4.500  -0.1467   0.05540   0.05060  -0.0592   0.9646   0.0566
  -4.250  -0.0962   0.05149   0.04616  -0.0685   0.9554   0.0637
  -4.000  -0.0728   0.04764   0.04244  -0.0699   0.9484   0.0664
  -3.750  -0.0310   0.04440   0.03886  -0.0753   0.9402   0.0780
  -3.500   0.0070   0.04236   0.03644  -0.0789   0.9310   0.0909
  -3.250   0.0372   0.03850   0.03274  -0.0812   0.9243   0.0959
  -2.750   0.1089   0.03380   0.02771  -0.0869   0.9078   0.1395
  -2.250   0.1916   0.02882   0.02175  -0.0909   0.8922   0.1030
  -2.000   0.2287   0.02579   0.01810  -0.0906   0.8822   0.0597
  -1.750   0.2654   0.02419   0.01618  -0.0919   0.8737   0.0596
  -1.500   0.2976   0.02276   0.01449  -0.0923   0.8624   0.0577
  -1.250   0.3291   0.02155   0.01298  -0.0924   0.8496   0.0551
  -1.000   0.3613   0.02058   0.01170  -0.0924   0.8358   0.0533
  -0.750   0.3928   0.01983   0.01070  -0.0924   0.8202   0.0523
  -0.500   0.4236   0.01895   0.00970  -0.0925   0.8025   0.0527
  -0.250   0.4547   0.01813   0.00883  -0.0927   0.7830   0.0547
   0.000   0.4840   0.01751   0.00812  -0.0924   0.7599   0.0552
   0.250   0.5150   0.01694   0.00743  -0.0924   0.7352   0.0550
   0.500   0.5445   0.01647   0.00686  -0.0922   0.7068   0.0550
   0.750   0.5734   0.01612   0.00636  -0.0919   0.6757   0.0554
   1.000   0.6012   0.01592   0.00597  -0.0914   0.6434   0.0559
   1.250   0.6271   0.01587   0.00570  -0.0906   0.6123   0.0568
   1.500   0.6526   0.01592   0.00554  -0.0898   0.5832   0.0598
   1.750   0.6781   0.01603   0.00543  -0.0891   0.5563   0.0625
   2.250   0.7284   0.01628   0.00532  -0.0876   0.5075   0.0671
   2.500   0.7533   0.01648   0.00535  -0.0868   0.4863   0.0712
   2.750   0.7782   0.01668   0.00544  -0.0861   0.4677   0.0803
   3.000   0.8085   0.01521   0.00571  -0.0868   0.4516   1.0000
   3.500   0.8574   0.01588   0.00605  -0.0853   0.4243   1.0000
   3.750   0.8818   0.01622   0.00627  -0.0846   0.4124   1.0000
   4.000   0.9064   0.01658   0.00653  -0.0839   0.4027   1.0000
   4.250   0.9307   0.01694   0.00680  -0.0832   0.3930   1.0000
   4.500   0.9550   0.01730   0.00711  -0.0826   0.3830   1.0000
   4.750   0.9790   0.01769   0.00741  -0.0819   0.3740   1.0000
   5.000   1.0029   0.01805   0.00778  -0.0811   0.3637   1.0000
   5.250   1.0265   0.01845   0.00815  -0.0804   0.3542   1.0000
   5.500   1.0499   0.01885   0.00852  -0.0796   0.3448   1.0000
   5.750   1.0733   0.01923   0.00896  -0.0789   0.3352   1.0000
   6.000   1.0962   0.01966   0.00935  -0.0780   0.3263   1.0000
   6.250   1.1194   0.02004   0.00982  -0.0772   0.3168   1.0000
   6.500   1.1420   0.02047   0.01029  -0.0764   0.3083   1.0000
   6.750   1.1642   0.02087   0.01077  -0.0755   0.2981   1.0000
   7.000   1.1863   0.02127   0.01128  -0.0745   0.2879   1.0000
   7.250   1.2076   0.02170   0.01176  -0.0735   0.2779   1.0000
   7.500   1.2283   0.02210   0.01227  -0.0723   0.2656   1.0000
   7.750   1.2488   0.02250   0.01279  -0.0712   0.2520   1.0000
   8.000   1.2688   0.02295   0.01332  -0.0700   0.2383   1.0000
   8.250   1.2882   0.02344   0.01390  -0.0687   0.2249   1.0000
   8.500   1.3066   0.02400   0.01453  -0.0673   0.2113   1.0000
   8.750   1.3235   0.02465   0.01520  -0.0657   0.1978   1.0000
   9.000   1.3389   0.02542   0.01597  -0.0640   0.1852   1.0000
   9.250   1.3532   0.02629   0.01687  -0.0621   0.1734   1.0000
   9.500   1.3658   0.02728   0.01790  -0.0601   0.1631   1.0000
   9.750   1.3778   0.02830   0.01898  -0.0580   0.1532   1.0000
  10.000   1.3894   0.02929   0.02010  -0.0558   0.1449   1.0000
  10.250   1.3987   0.03035   0.02125  -0.0534   0.1377   1.0000
  10.500   1.4090   0.03142   0.02246  -0.0511   0.1316   1.0000
  10.750   1.4181   0.03252   0.02371  -0.0489   0.1258   1.0000
  11.000   1.4258   0.03369   0.02497  -0.0466   0.1204   1.0000
  11.250   1.4332   0.03484   0.02627  -0.0444   0.1137   1.0000
  11.500   1.4382   0.03616   0.02767  -0.0423   0.1076   1.0000
  11.750   1.4417   0.03765   0.02924  -0.0403   0.1016   1.0000
  12.000   1.4432   0.03938   0.03104  -0.0383   0.0972   1.0000
  12.250   1.4452   0.04122   0.03306  -0.0366   0.0932   1.0000
  12.500   1.4432   0.04344   0.03535  -0.0351   0.0895   1.0000
  12.750   1.4403   0.04591   0.03789  -0.0338   0.0861   1.0000
  13.000   1.4391   0.04843   0.04065  -0.0329   0.0819   1.0000
  13.250   1.4342   0.05144   0.04380  -0.0323   0.0784   1.0000
  13.500   1.4263   0.05493   0.04735  -0.0321   0.0755   1.0000
  13.750   1.4214   0.05844   0.05110  -0.0324   0.0719   1.0000
  14.000   1.4147   0.06240   0.05532  -0.0332   0.0680   1.0000
  14.250   1.4046   0.06700   0.06010  -0.0345   0.0648   1.0000
  14.500   1.3918   0.07217   0.06537  -0.0363   0.0623   1.0000
  14.750   1.3831   0.07719   0.07070  -0.0382   0.0587   1.0000
  15.000   1.3708   0.08297   0.07670  -0.0406   0.0551   1.0000
  15.250   1.3559   0.08933   0.08321  -0.0436   0.0525   1.0000
  15.500   1.3417   0.09581   0.08985  -0.0466   0.0496   1.0000
  15.750   1.3281   0.10236   0.09660  -0.0497   0.0463   1.0000
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