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GOE 624 AIRFOIL (goe624-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 624 AIRFOIL (goe624-il)
Reynolds number: 50,000
Max Cl/Cd: 22.81 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe624-il-50000-n5.txt
Download as CSV file: xf-goe624-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 624 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2667   0.13335   0.12641  -0.0450   1.0000   0.1343
 -10.750  -0.2770   0.13188   0.12504  -0.0436   1.0000   0.1344
 -10.250  -0.2972   0.12254   0.11580  -0.0423   1.0000   0.0945
 -10.000  -0.2882   0.11953   0.11278  -0.0427   0.9967   0.0921
  -9.750  -0.2741   0.11515   0.10838  -0.0467   0.9899   0.0910
  -9.500  -0.2612   0.11063   0.10384  -0.0510   0.9831   0.0896
  -9.250  -0.2524   0.10588   0.09908  -0.0555   0.9751   0.0876
  -9.000  -0.2677   0.09780   0.09098  -0.0647   0.9648   0.0830
  -8.750  -0.2545   0.09347   0.08663  -0.0687   0.9574   0.0824
  -8.500  -0.2484   0.08906   0.08221  -0.0727   0.9477   0.0819
  -8.250  -0.2450   0.08351   0.07663  -0.0790   0.9387   0.0817
  -8.000  -0.2482   0.07759   0.07065  -0.0848   0.9266   0.0817
  -7.750  -0.2543   0.07182   0.06474  -0.0892   0.9148   0.0818
  -7.500  -0.2544   0.06531   0.05794  -0.0945   0.9063   0.0822
  -7.250  -0.2603   0.06070   0.05303  -0.0955   0.8939   0.0824
  -7.000  -0.2536   0.05549   0.04731  -0.0979   0.8862   0.0828
  -6.750  -0.2452   0.05242   0.04396  -0.0977   0.8758   0.0835
  -6.500  -0.2189   0.04991   0.04126  -0.0994   0.8704   0.0848
  -6.250  -0.2071   0.04829   0.03946  -0.0982   0.8595   0.0864
  -6.000  -0.1818   0.04575   0.03655  -0.0994   0.8533   0.0893
  -5.750  -0.1672   0.04346   0.03377  -0.0987   0.8432   0.0921
  -5.500  -0.1409   0.04110   0.03096  -0.0993   0.8363   0.0948
  -5.250  -0.1170   0.03981   0.02954  -0.0991   0.8279   0.0974
  -5.000  -0.0922   0.03848   0.02796  -0.0989   0.8195   0.1018
  -4.750  -0.0585   0.03676   0.02588  -0.0999   0.8144   0.1079
  -4.500  -0.0415   0.03618   0.02524  -0.0984   0.8032   0.1125
  -4.250  -0.0090   0.03485   0.02359  -0.0990   0.7975   0.1209
  -4.000   0.0111   0.03439   0.02316  -0.0979   0.7876   0.1280
  -3.750   0.0407   0.03354   0.02216  -0.0981   0.7808   0.1386
  -3.500   0.0668   0.03300   0.02145  -0.0977   0.7731   0.1510
  -3.000   0.1249   0.03182   0.02023  -0.0977   0.7596   0.1781
  -2.750   0.1437   0.03169   0.02009  -0.0964   0.7487   0.1898
  -2.500   0.1765   0.03103   0.01932  -0.0967   0.7429   0.2057
  -2.250   0.1978   0.03091   0.01915  -0.0957   0.7332   0.2209
  -2.000   0.2272   0.03036   0.01863  -0.0956   0.7266   0.2410
  -1.750   0.2512   0.03005   0.01841  -0.0950   0.7183   0.2651
  -1.500   0.2765   0.02964   0.01814  -0.0944   0.7104   0.3011
  -1.250   0.3078   0.02879   0.01756  -0.0946   0.7056   0.3664
  -1.000   0.3216   0.02868   0.01793  -0.0925   0.6946   0.4555
  -0.750   0.3439   0.02759   0.01775  -0.0898   0.6895   0.6682
  -0.500   0.4092   0.02739   0.01785  -0.0955   0.6805   0.9955
  -0.250   0.4367   0.02743   0.01757  -0.0952   0.6736   1.0000
   0.000   0.4564   0.02778   0.01769  -0.0940   0.6652   1.0000
   0.250   0.4791   0.02802   0.01771  -0.0932   0.6573   1.0000
   0.500   0.5109   0.02788   0.01730  -0.0933   0.6525   1.0000
   0.750   0.5222   0.02871   0.01803  -0.0912   0.6415   1.0000
   1.000   0.5528   0.02868   0.01778  -0.0913   0.6364   1.0000
   1.250   0.5666   0.02948   0.01848  -0.0896   0.6267   1.0000
   1.500   0.5936   0.02965   0.01848  -0.0893   0.6205   1.0000
   1.750   0.6181   0.02998   0.01866  -0.0887   0.6141   1.0000
   2.000   0.6337   0.03077   0.01938  -0.0873   0.6052   1.0000
   2.250   0.6647   0.03079   0.01924  -0.0874   0.6006   1.0000
   2.500   0.6755   0.03190   0.02032  -0.0855   0.5914   1.0000
   2.750   0.7002   0.03226   0.02058  -0.0851   0.5853   1.0000
   3.000   0.7338   0.03217   0.02034  -0.0855   0.5815   1.0000
   3.250   0.7350   0.03388   0.02208  -0.0828   0.5711   1.0000
   3.500   0.7637   0.03405   0.02216  -0.0827   0.5663   1.0000
   3.750   0.7806   0.03493   0.02299  -0.0816   0.5598   1.0000
   4.000   0.7914   0.03615   0.02421  -0.0798   0.5518   1.0000
   4.250   0.8230   0.03616   0.02415  -0.0801   0.5479   1.0000
   4.500   0.8214   0.03820   0.02622  -0.0773   0.5388   1.0000
   4.750   0.8424   0.03882   0.02681  -0.0766   0.5332   1.0000
   5.000   0.8777   0.03860   0.02653  -0.0771   0.5299   1.0000
   5.250   0.8564   0.04184   0.02985  -0.0728   0.5188   1.0000
   5.500   0.8862   0.04190   0.02987  -0.0727   0.5147   1.0000
   5.750   0.9112   0.04229   0.03024  -0.0723   0.5102   1.0000
   6.000   0.8919   0.04579   0.03382  -0.0689   0.4994   1.0000
   6.250   0.9284   0.04523   0.03323  -0.0691   0.4964   1.0000
   6.750   0.9315   0.04964   0.03771  -0.0657   0.4804   1.0000
   7.000   0.9650   0.04917   0.03723  -0.0656   0.4772   1.0000
   7.500   0.9543   0.05518   0.04335  -0.0624   0.4585   1.0000
   8.000   0.9326   0.06313   0.05143  -0.0602   0.4366   1.0000
   8.250   0.9509   0.06386   0.05219  -0.0594   0.4307   1.0000
   8.500   0.9848   0.06279   0.05113  -0.0586   0.4280   1.0000
   9.000   0.9884   0.06814   0.05659  -0.0571   0.4109   1.0000
   9.250   1.0255   0.06661   0.05509  -0.0562   0.4090   1.0000
   9.750   1.0237   0.07267   0.06127  -0.0549   0.3914   1.0000
  10.250   1.0229   0.07886   0.06758  -0.0539   0.3743   1.0000
  10.500   0.9924   0.08615   0.07498  -0.0544   0.3599   1.0000
  10.750   1.0209   0.08548   0.07435  -0.0534   0.3575   1.0000
  11.000   0.9913   0.09281   0.08177  -0.0541   0.3437   1.0000
  11.250   1.0196   0.09209   0.08110  -0.0531   0.3412   1.0000
  11.500   0.9889   0.09982   0.08891  -0.0542   0.3279   1.0000
  11.750   1.0137   0.09967   0.08882  -0.0533   0.3254   1.0000
  12.000   0.9827   0.10773   0.09694  -0.0549   0.3130   1.0000
  12.250   1.0065   0.10766   0.09695  -0.0541   0.3101   1.0000
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