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GOE 372 AIRFOIL (goe372-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 372 AIRFOIL (goe372-il)
Reynolds number: 50,000
Max Cl/Cd: 43.2 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe372-il-50000.txt
Download as CSV file: xf-goe372-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 372 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3637   0.10391   0.09732  -0.0264   1.0000   0.1447
  -7.500  -0.3519   0.09896   0.09240  -0.0251   1.0000   0.1508
  -7.250  -0.3570   0.09741   0.09097  -0.0245   1.0000   0.1567
  -7.000  -0.3685   0.09747   0.09120  -0.0275   1.0000   0.1592
  -6.750  -0.3548   0.09192   0.08566  -0.0235   1.0000   0.1676
  -6.500  -0.3633   0.09153   0.08541  -0.0268   1.0000   0.1727
  -6.250  -0.3555   0.08695   0.08088  -0.0234   1.0000   0.1785
  -6.000  -0.3585   0.08570   0.07972  -0.0256   1.0000   0.1861
  -5.500  -0.3556   0.08137   0.07550  -0.0283   1.0000   0.2011
  -5.250  -0.3518   0.07698   0.07119  -0.0222   1.0000   0.2086
  -5.000  -0.3494   0.07448   0.06873  -0.0230   1.0000   0.2182
  -4.750  -0.3450   0.07202   0.06629  -0.0236   1.0000   0.2310
  -4.500  -0.3415   0.06922   0.06349  -0.0214   1.0000   0.2474
  -4.250  -0.3346   0.06698   0.06124  -0.0227   1.0000   0.2717
  -4.000  -0.3311   0.06396   0.05828  -0.0193   1.0000   0.2900
  -3.750  -0.3234   0.06132   0.05564  -0.0190   1.0000   0.3154
  -3.500  -0.3172   0.05861   0.05295  -0.0170   1.0000   0.3440
  -3.250  -0.3111   0.05619   0.05055  -0.0151   1.0000   0.3834
  -3.000  -0.3101   0.05361   0.04804  -0.0104   1.0000   0.4258
  -2.000  -0.0877   0.03690   0.02875  -0.0547   1.0000   0.2107
  -1.750  -0.0581   0.03471   0.02615  -0.0563   1.0000   0.2088
  -1.500  -0.0252   0.03249   0.02329  -0.0580   1.0000   0.1971
  -1.250   0.0024   0.03081   0.02116  -0.0587   1.0000   0.1939
  -1.000   0.0287   0.02953   0.01946  -0.0590   1.0000   0.1956
  -0.750   0.0535   0.02857   0.01807  -0.0590   1.0000   0.2024
  -0.500   0.0737   0.02799   0.01740  -0.0587   1.0000   0.2207
  -0.250   0.0960   0.02744   0.01665  -0.0584   1.0000   0.2350
   0.000   0.1204   0.02716   0.01611  -0.0586   1.0000   0.2573
   0.250   0.1439   0.02702   0.01586  -0.0588   1.0000   0.2843
   0.500   0.1676   0.02690   0.01580  -0.0591   1.0000   0.3160
   0.750   0.2012   0.02684   0.01585  -0.0612   0.9964   0.3675
   1.000   0.2519   0.02521   0.01554  -0.0659   0.9855   1.0000
   1.250   0.2967   0.02636   0.01615  -0.0702   0.9724   1.0000
   1.500   0.3378   0.02742   0.01694  -0.0739   0.9591   1.0000
   1.750   0.3757   0.02842   0.01776  -0.0771   0.9463   1.0000
   2.000   0.4118   0.02940   0.01862  -0.0798   0.9337   1.0000
   2.250   0.4463   0.03037   0.01951  -0.0822   0.9214   1.0000
   2.500   0.4797   0.03134   0.02045  -0.0843   0.9096   1.0000
   2.750   0.5137   0.03232   0.02144  -0.0865   0.8983   1.0000
   3.000   0.5499   0.03328   0.02243  -0.0889   0.8874   1.0000
   3.250   0.5751   0.03426   0.02345  -0.0896   0.8754   1.0000
   3.500   0.6008   0.03528   0.02454  -0.0903   0.8634   1.0000
   3.750   0.6279   0.03630   0.02571  -0.0911   0.8512   1.0000
   4.000   0.6642   0.03701   0.02657  -0.0928   0.8356   1.0000
   4.250   0.7095   0.03727   0.02705  -0.0949   0.8164   1.0000
   4.500   0.7408   0.03772   0.02770  -0.0952   0.7970   1.0000
   4.750   0.7790   0.03805   0.02838  -0.0963   0.7804   1.0000
   5.000   0.8366   0.03738   0.02815  -0.0988   0.7626   1.0000
   5.250   0.9465   0.02750   0.01904  -0.0944   0.6868   1.0000
   5.500   0.9784   0.02440   0.01611  -0.0883   0.6294   1.0000
   5.750   0.9961   0.02306   0.01474  -0.0822   0.5613   1.0000
   6.000   0.9991   0.02313   0.01407  -0.0751   0.4143   1.0000
   6.250   0.9912   0.02603   0.01517  -0.0696   0.1780   1.0000
   6.500   0.9944   0.02890   0.01725  -0.0666   0.1082   1.0000
   6.750   1.0041   0.03090   0.01917  -0.0638   0.0944   1.0000
   7.000   1.0152   0.03274   0.02107  -0.0612   0.0878   1.0000
   7.250   1.0289   0.03453   0.02305  -0.0588   0.0831   1.0000
   7.500   1.0507   0.03664   0.02514  -0.0571   0.0796   1.0000
   7.750   1.0910   0.03889   0.02757  -0.0570   0.0765   1.0000
   8.000   1.1292   0.04159   0.03046  -0.0572   0.0727   1.0000
   8.250   1.1635   0.04493   0.03411  -0.0570   0.0717   1.0000
   8.500   1.1898   0.04880   0.03852  -0.0559   0.0734   1.0000
   8.750   1.2093   0.05301   0.04324  -0.0544   0.0756   1.0000
   9.000   1.2253   0.05760   0.04820  -0.0529   0.0778   1.0000
   9.250   1.2381   0.06199   0.05310  -0.0510   0.0803   1.0000
   9.500   1.2252   0.06616   0.05816  -0.0471   0.0839   1.0000
   9.750   1.2173   0.07098   0.06343  -0.0446   0.0870   1.0000
  10.000   1.2166   0.07626   0.06892  -0.0431   0.0900   1.0000
  10.250   1.2056   0.08070   0.07371  -0.0410   0.0930   1.0000
  10.500   1.1738   0.08445   0.07776  -0.0383   0.0941   1.0000
  10.750   1.1430   0.08887   0.08237  -0.0374   0.0947   1.0000
  11.000   1.1122   0.09427   0.08783  -0.0386   0.0951   1.0000
  11.250   1.0801   0.10106   0.09471  -0.0421   0.0955   1.0000
  11.500   1.0475   0.10969   0.10338  -0.0480   0.0962   1.0000
  11.750   1.0195   0.12021   0.11387  -0.0556   0.0987   1.0000
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