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GOE 424 AIRFOIL (goe424-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 424 AIRFOIL (goe424-il)
Reynolds number: 50,000
Max Cl/Cd: 3.63 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe424-il-50000.txt
Download as CSV file: xf-goe424-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 424 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2571   0.13914   0.13332  -0.0283   1.0000   0.2982
 -10.750  -0.2860   0.14099   0.13538  -0.0238   1.0000   0.3037
 -10.500  -0.3372   0.14503   0.13968  -0.0191   1.0000   0.3066
 -10.250  -0.2866   0.13839   0.13295  -0.0243   0.9931   0.3184
 -10.000  -0.2619   0.13366   0.12818  -0.0301   0.9841   0.3303
  -9.500  -0.2169   0.12536   0.11980  -0.0407   0.9669   0.3553
  -9.250  -0.1917   0.12083   0.11522  -0.0452   0.9568   0.3657
  -9.000  -0.1857   0.11787   0.11227  -0.0485   0.9464   0.3792
  -8.750  -0.1838   0.11571   0.11010  -0.0523   0.9385   0.3947
  -8.500  -0.1478   0.11007   0.10440  -0.0559   0.9276   0.3977
  -8.250  -0.3650   0.08873   0.08322  -0.0732   0.9106   0.1965
  -8.000  -0.4459   0.08150   0.07575  -0.0726   0.8977   0.1827
  -7.750  -0.4721   0.07481   0.06870  -0.0732   0.8899   0.1720
  -7.500  -0.4954   0.07177   0.06532  -0.0698   0.8807   0.1667
  -7.250  -0.4886   0.06775   0.06101  -0.0699   0.8744   0.1622
  -7.000  -0.4967   0.06449   0.05727  -0.0677   0.8677   0.1585
  -6.750  -0.4990   0.06158   0.05376  -0.0655   0.8610   0.1558
  -6.500  -0.4768   0.05864   0.05019  -0.0663   0.8559   0.1551
  -6.250  -0.4756   0.05745   0.04863  -0.0634   0.8499   0.1545
  -6.000  -0.4627   0.05611   0.04689  -0.0621   0.8451   0.1539
  -5.750  -0.4357   0.05433   0.04477  -0.0627   0.8406   0.1542
  -5.500  -0.4112   0.05307   0.04339  -0.0630   0.8362   0.1567
  -5.250  -0.4034   0.05267   0.04290  -0.0609   0.8314   0.1586
  -5.000  -0.3835   0.05205   0.04209  -0.0603   0.8271   0.1610
  -4.750  -0.3555   0.05138   0.04120  -0.0608   0.8235   0.1633
  -4.500  -0.3225   0.05091   0.04046  -0.0618   0.8202   0.1674
  -4.250  -0.3176   0.05110   0.04059  -0.0593   0.8175   0.1704
  -4.000  -0.3069   0.05119   0.04076  -0.0576   0.8147   0.1748
  -3.750  -0.2920   0.05136   0.04090  -0.0563   0.8124   0.1799
  -3.500  -0.2772   0.05170   0.04109  -0.0551   0.8115   0.1851
  -3.250  -0.4692   0.05375   0.04340  -0.0293   0.9679   0.1662
  -3.000  -0.4716   0.05270   0.04224  -0.0252   0.9749   0.1685
  -2.750  -0.4514   0.05269   0.04234  -0.0250   0.9743   0.1737
  -2.500  -0.4251   0.05318   0.04279  -0.0256   0.9715   0.1804
  -2.250  -0.3939   0.05414   0.04373  -0.0271   0.9686   0.1884
  -2.000  -0.3743   0.05442   0.04398  -0.0269   0.9669   0.1996
  -1.750  -0.3556   0.05438   0.04403  -0.0266   0.9630   0.2156
  -1.500  -0.3284   0.05455   0.04456  -0.0280   0.9586   0.2540
  -1.250  -0.3066   0.05403   0.04629  -0.0271   0.9563   0.5891
  -1.000  -0.2911   0.05564   0.04852  -0.0226   0.9533   0.7499
  -0.750  -0.2911   0.05550   0.04866  -0.0162   0.9471   0.8381
  -0.500  -0.2350   0.05872   0.05182  -0.0205   0.9408   0.9590
  -0.250  -0.1747   0.06174   0.05445  -0.0297   0.9361   1.0000
   0.000  -0.1665   0.06156   0.05398  -0.0291   0.9248   1.0000
   0.250  -0.1534   0.06234   0.05446  -0.0291   0.9186   1.0000
   0.500  -0.1333   0.06327   0.05510  -0.0300   0.9087   1.0000
   0.750  -0.1132   0.06479   0.05634  -0.0309   0.9027   1.0000
   1.000  -0.0918   0.06589   0.05719  -0.0318   0.8919   1.0000
   1.250  -0.0736   0.06733   0.05841  -0.0323   0.8853   1.0000
   1.500  -0.0506   0.06875   0.05961  -0.0334   0.8751   1.0000
   1.750  -0.0344   0.07007   0.06074  -0.0334   0.8674   1.0000
   2.000  -0.0072   0.07199   0.06246  -0.0352   0.8575   1.0000
   2.250   0.0043   0.07298   0.06331  -0.0345   0.8486   1.0000
   2.500   0.0346   0.07536   0.06550  -0.0367   0.8399   1.0000
   2.750   0.0433   0.07612   0.06615  -0.0355   0.8295   1.0000
   3.000   0.0781   0.07913   0.06898  -0.0384   0.8217   1.0000
   3.250   0.0821   0.07948   0.06925  -0.0366   0.8104   1.0000
   3.500   0.1207   0.08313   0.07273  -0.0400   0.8036   1.0000
   3.750   0.1217   0.08308   0.07262  -0.0377   0.7908   1.0000
   4.000   0.1545   0.08657   0.07597  -0.0404   0.7848   1.0000
   4.250   0.1613   0.08694   0.07628  -0.0389   0.7715   1.0000
   4.500   0.1729   0.08851   0.07779  -0.0385   0.7620   1.0000
   4.750   0.2028   0.09122   0.08040  -0.0404   0.7521   1.0000
   5.000   0.2064   0.09207   0.08121  -0.0389   0.7405   1.0000
   5.250   0.2458   0.09605   0.08509  -0.0421   0.7332   1.0000
   5.500   0.2437   0.09614   0.08516  -0.0398   0.7197   1.0000
   5.750   0.2597   0.09846   0.08742  -0.0401   0.7116   1.0000
   6.000   0.2828   0.10068   0.08960  -0.0410   0.6999   1.0000
   6.250   0.2861   0.10189   0.09078  -0.0398   0.6885   1.0000
   6.500   0.3228   0.10574   0.09457  -0.0425   0.6808   1.0000
   6.750   0.3186   0.10611   0.09494  -0.0404   0.6679   1.0000
   7.000   0.3491   0.10999   0.09877  -0.0424   0.6616   1.0000
   7.250   0.3507   0.11060   0.09938  -0.0410   0.6485   1.0000
   7.500   0.3610   0.11292   0.10170  -0.0409   0.6408   1.0000
   7.750   0.3808   0.11519   0.10394  -0.0415   0.6297   1.0000
   8.000   0.3839   0.11696   0.10571  -0.0408   0.6208   1.0000
   8.250   0.4065   0.11965   0.10840  -0.0418   0.6117   1.0000
   8.500   0.4116   0.12182   0.11057  -0.0414   0.6048   1.0000
   8.750   0.4276   0.12394   0.11269  -0.0418   0.5945   1.0000
   9.000   0.4450   0.12729   0.11604  -0.0426   0.5891   1.0000
   9.250   0.4471   0.12824   0.11702  -0.0418   0.5778   1.0000
   9.500   0.4825   0.13308   0.12186  -0.0441   0.5732   1.0000
   9.750   0.4649   0.13277   0.12157  -0.0421   0.5638   1.0000
  10.000   0.4915   0.13621   0.12502  -0.0434   0.5568   1.0000
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