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GOE 373 AIRFOIL (goe373-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 373 AIRFOIL (goe373-il)
Reynolds number: 50,000
Max Cl/Cd: 35.5 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe373-il-50000.txt
Download as CSV file: xf-goe373-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 373 AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3123   0.10943   0.10257  -0.0213   1.0000   0.1031
  -8.250  -0.3154   0.10863   0.10188  -0.0224   1.0000   0.1059
  -8.000  -0.3266   0.10929   0.10270  -0.0237   1.0000   0.1070
  -7.750  -0.3056   0.10203   0.09543  -0.0218   1.0000   0.1125
  -7.500  -0.3049   0.09996   0.09345  -0.0214   1.0000   0.1175
  -7.250  -0.3107   0.09946   0.09310  -0.0229   1.0000   0.1208
  -7.000  -0.3153   0.10054   0.09430  -0.0289   1.0000   0.1221
  -6.750  -0.3003   0.09275   0.08652  -0.0214   1.0000   0.1288
  -6.500  -0.2992   0.09108   0.08495  -0.0227   1.0000   0.1344
  -6.250  -0.2992   0.09154   0.08552  -0.0293   1.0000   0.1373
  -6.000  -0.2927   0.08568   0.07974  -0.0224   1.0000   0.1428
  -5.750  -0.2900   0.08405   0.07818  -0.0238   1.0000   0.1499
  -5.500  -0.2870   0.08187   0.07608  -0.0254   1.0000   0.1540
  -5.250  -0.2844   0.07887   0.07316  -0.0223   1.0000   0.1613
  -5.000  -0.2789   0.07739   0.07171  -0.0259   1.0000   0.1687
  -4.750  -0.2778   0.07449   0.06889  -0.0224   1.0000   0.1773
  -4.500  -0.2731   0.07219   0.06663  -0.0229   1.0000   0.1863
  -4.250  -0.2656   0.07012   0.06456  -0.0244   1.0000   0.1990
  -3.500  -0.2436   0.06300   0.05752  -0.0239   1.0000   0.2438
  -3.250  -0.2372   0.06058   0.05515  -0.0226   1.0000   0.2624
  -3.000  -0.2273   0.05839   0.05298  -0.0229   1.0000   0.2893
  -2.750  -0.2209   0.05618   0.05083  -0.0214   1.0000   0.3202
  -2.500  -0.2173   0.05404   0.04876  -0.0186   1.0000   0.3555
  -1.750  -0.2236   0.04798   0.04306  -0.0039   1.0000   0.5151
  -1.500  -0.2283   0.04593   0.04115   0.0023   1.0000   0.5626
  -1.250  -0.2209   0.04353   0.03887   0.0073   0.9930   0.6246
  -1.000  -0.2003   0.04087   0.03629   0.0101   0.9791   0.6870
  -0.750  -0.1674   0.03835   0.03378   0.0087   0.9641   0.7324
  -0.500  -0.1054   0.03604   0.03136  -0.0013   0.9476   0.7551
  -0.250   0.2241   0.03636   0.02868  -0.0810   0.9233   0.3131
   0.000   0.2889   0.03560   0.02710  -0.0871   0.9072   0.2375
   0.250   0.3438   0.03501   0.02582  -0.0909   0.8915   0.1966
   0.500   0.3919   0.03393   0.02446  -0.0939   0.8765   0.1778
   0.750   0.4397   0.03320   0.02337  -0.0965   0.8615   0.1644
   1.000   0.4905   0.03239   0.02221  -0.0995   0.8471   0.1553
   1.250   0.5412   0.03173   0.02126  -0.1022   0.8331   0.1527
   1.500   0.5864   0.03094   0.02041  -0.1042   0.8187   0.1558
   1.750   0.6261   0.03043   0.01985  -0.1052   0.8039   0.1582
   2.000   0.6621   0.03012   0.01950  -0.1057   0.7886   0.1621
   2.250   0.6955   0.02998   0.01934  -0.1058   0.7731   0.1704
   2.500   0.7276   0.02990   0.01934  -0.1058   0.7580   0.1899
   2.750   0.7628   0.02839   0.01932  -0.1061   0.7441   1.0000
   3.000   0.7916   0.02886   0.01947  -0.1052   0.7294   1.0000
   3.250   0.8208   0.02928   0.01965  -0.1045   0.7156   1.0000
   3.500   0.8450   0.02999   0.02022  -0.1035   0.7009   1.0000
   3.750   0.8679   0.03080   0.02096  -0.1025   0.6865   1.0000
   4.000   0.8898   0.03170   0.02180  -0.1015   0.6724   1.0000
   4.250   0.9128   0.03243   0.02250  -0.1004   0.6580   1.0000
   4.500   0.9391   0.03268   0.02269  -0.0990   0.6426   1.0000
   4.750   0.9668   0.03268   0.02268  -0.0975   0.6269   1.0000
   5.000   0.9938   0.03272   0.02269  -0.0960   0.6112   1.0000
   5.250   1.0183   0.03312   0.02310  -0.0947   0.5963   1.0000
   5.500   1.0415   0.03372   0.02375  -0.0934   0.5818   1.0000
   5.750   1.0647   0.03434   0.02446  -0.0920   0.5671   1.0000
   6.000   1.0884   0.03490   0.02508  -0.0907   0.5521   1.0000
   6.250   1.1127   0.03542   0.02567  -0.0893   0.5366   1.0000
   6.500   1.1364   0.03599   0.02632  -0.0878   0.5203   1.0000
   6.750   1.1532   0.03719   0.02772  -0.0861   0.5021   1.0000
   7.000   1.1726   0.03817   0.02884  -0.0844   0.4836   1.0000
   7.250   1.1958   0.03879   0.02955  -0.0828   0.4650   1.0000
   7.500   1.2230   0.03906   0.02986  -0.0813   0.4467   1.0000
   7.750   1.2404   0.04013   0.03108  -0.0794   0.4273   1.0000
   8.000   1.2631   0.04008   0.03113  -0.0774   0.4054   1.0000
   8.250   1.2883   0.03918   0.03018  -0.0752   0.3813   1.0000
   8.500   1.3180   0.03759   0.02836  -0.0733   0.3568   1.0000
   8.750   1.3325   0.03846   0.02943  -0.0713   0.3382   1.0000
   9.000   1.3497   0.03923   0.03041  -0.0695   0.3214   1.0000
   9.250   1.3668   0.03938   0.03065  -0.0674   0.3023   1.0000
   9.500   1.3822   0.03893   0.03017  -0.0650   0.2808   1.0000
   9.750   1.3915   0.03966   0.03116  -0.0625   0.2630   1.0000
  10.000   1.3982   0.03999   0.03164  -0.0595   0.2427   1.0000
  10.250   1.3958   0.04052   0.03227  -0.0559   0.2193   1.0000
  10.500   1.3891   0.04161   0.03334  -0.0520   0.1955   1.0000
  10.750   1.3757   0.04369   0.03534  -0.0479   0.1723   1.0000
  11.000   1.3591   0.04679   0.03828  -0.0445   0.1487   1.0000
  11.250   1.3439   0.05037   0.04167  -0.0420   0.1286   1.0000
  11.500   1.3337   0.05394   0.04514  -0.0405   0.1140   1.0000
  11.750   1.3269   0.05757   0.04882  -0.0395   0.1028   1.0000
  12.000   1.3238   0.06116   0.05251  -0.0387   0.0943   1.0000
  12.250   1.3256   0.06417   0.05538  -0.0378   0.0876   1.0000
  12.500   1.3282   0.06795   0.05950  -0.0369   0.0828   1.0000
  12.750   1.3340   0.07124   0.06291  -0.0361   0.0788   1.0000
  13.000   1.3474   0.07450   0.06619  -0.0347   0.0755   1.0000
  13.250   1.3382   0.07966   0.07172  -0.0352   0.0747   1.0000
  13.500   1.3246   0.08539   0.07777  -0.0365   0.0744   1.0000
  13.750   1.3068   0.09183   0.08450  -0.0387   0.0744   1.0000
  14.000   1.2857   0.09904   0.09197  -0.0418   0.0747   1.0000
  14.250   1.2632   0.10697   0.10010  -0.0458   0.0752   1.0000
  14.500   1.2400   0.11557   0.10886  -0.0505   0.0758   1.0000
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