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GOE 389 AIRFOIL (goe389-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 389 AIRFOIL (goe389-il)
Reynolds number: 200,000
Max Cl/Cd: 75.14 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe389-il-200000.txt
Download as CSV file: xf-goe389-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 389 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3652   0.08801   0.08476  -0.0361   1.0000   0.0574
  -7.750  -0.3849   0.08586   0.08272  -0.0380   1.0000   0.0579
  -7.500  -0.4019   0.08319   0.08011  -0.0400   1.0000   0.0582
  -7.250  -0.4148   0.08032   0.07724  -0.0409   1.0000   0.0583
  -7.000  -0.4148   0.07505   0.07204  -0.0393   0.9986   0.0594
  -6.750  -0.3915   0.07263   0.06963  -0.0381   0.9956   0.0610
  -6.500  -0.3614   0.06875   0.06571  -0.0431   0.9904   0.0639
  -6.250  -0.3161   0.05638   0.05278  -0.0665   0.9800   0.0722
  -6.000  -0.2903   0.05423   0.05080  -0.0664   0.9755   0.0743
  -5.750  -0.2551   0.05091   0.04740  -0.0709   0.9716   0.0784
  -5.500  -0.2200   0.04358   0.03953  -0.0800   0.9621   0.0874
  -5.250  -0.1838   0.04109   0.03706  -0.0831   0.9587   0.0911
  -5.000  -0.1505   0.03722   0.03284  -0.0873   0.9507   0.1028
  -4.750  -0.1124   0.03434   0.02961  -0.0914   0.9462   0.1160
  -4.500  -0.0723   0.02485   0.01884  -0.0937   0.9413   0.0676
  -4.250  -0.0393   0.02244   0.01601  -0.0948   0.9343   0.0666
  -4.000  -0.0018   0.02011   0.01325  -0.0965   0.9301   0.0645
  -3.750   0.0290   0.01868   0.01153  -0.0968   0.9216   0.0642
  -3.500   0.0639   0.01747   0.01009  -0.0979   0.9158   0.0649
  -3.250   0.0932   0.01673   0.00922  -0.0978   0.9066   0.0672
  -3.000   0.1258   0.01588   0.00824  -0.0983   0.8998   0.0688
  -2.750   0.1527   0.01524   0.00750  -0.0977   0.8891   0.0701
  -2.500   0.1808   0.01462   0.00681  -0.0973   0.8798   0.0717
  -2.250   0.2080   0.01374   0.00597  -0.0970   0.8707   0.0754
  -2.000   0.2339   0.01329   0.00553  -0.0963   0.8595   0.0806
  -1.750   0.2604   0.01279   0.00503  -0.0958   0.8489   0.0900
  -1.500   0.2876   0.01218   0.00451  -0.0953   0.8391   0.1179
  -1.250   0.3112   0.01109   0.00433  -0.0948   0.8272   0.3508
  -1.000   0.3333   0.01030   0.00427  -0.0935   0.8150   0.5710
  -0.750   0.3768   0.00922   0.00412  -0.0953   0.8034   1.0000
  -0.500   0.4028   0.00924   0.00395  -0.0946   0.7900   1.0000
  -0.250   0.4289   0.00927   0.00380  -0.0939   0.7756   1.0000
   0.000   0.4549   0.00933   0.00368  -0.0932   0.7602   1.0000
   0.250   0.4809   0.00941   0.00360  -0.0925   0.7437   1.0000
   0.500   0.5067   0.00952   0.00355  -0.0918   0.7262   1.0000
   0.750   0.5324   0.00966   0.00351  -0.0911   0.7077   1.0000
   1.000   0.5579   0.00979   0.00351  -0.0904   0.6873   1.0000
   1.250   0.5832   0.00992   0.00351  -0.0897   0.6646   1.0000
   1.500   0.6085   0.01006   0.00351  -0.0890   0.6413   1.0000
   1.750   0.6338   0.01020   0.00350  -0.0883   0.6177   1.0000
   2.000   0.6591   0.01037   0.00353  -0.0877   0.5951   1.0000
   2.250   0.6843   0.01059   0.00358  -0.0871   0.5748   1.0000
   2.500   0.7097   0.01085   0.00367  -0.0865   0.5571   1.0000
   2.750   0.7351   0.01114   0.00380  -0.0860   0.5413   1.0000
   3.000   0.7608   0.01143   0.00398  -0.0855   0.5272   1.0000
   3.250   0.7868   0.01171   0.00419  -0.0852   0.5147   1.0000
   3.500   0.8130   0.01200   0.00443  -0.0849   0.5045   1.0000
   3.750   0.8393   0.01234   0.00467  -0.0846   0.4955   1.0000
   4.000   0.8655   0.01261   0.00495  -0.0843   0.4861   1.0000
   4.250   0.8918   0.01293   0.00523  -0.0841   0.4780   1.0000
   4.500   0.9181   0.01323   0.00551  -0.0838   0.4697   1.0000
   4.750   0.9442   0.01354   0.00583  -0.0836   0.4615   1.0000
   5.000   0.9703   0.01385   0.00613  -0.0833   0.4537   1.0000
   5.250   0.9962   0.01415   0.00647  -0.0830   0.4458   1.0000
   5.500   1.0221   0.01446   0.00676  -0.0827   0.4378   1.0000
   5.750   1.0473   0.01472   0.00711  -0.0822   0.4286   1.0000
   6.000   1.0713   0.01494   0.00733  -0.0816   0.4160   1.0000
   6.250   1.0946   0.01512   0.00753  -0.0808   0.4022   1.0000
   6.500   1.1185   0.01536   0.00777  -0.0801   0.3907   1.0000
   6.750   1.1418   0.01553   0.00801  -0.0793   0.3774   1.0000
   7.000   1.1643   0.01571   0.00822  -0.0784   0.3618   1.0000
   7.250   1.1873   0.01591   0.00850  -0.0776   0.3476   1.0000
   7.500   1.2102   0.01615   0.00883  -0.0768   0.3327   1.0000
   7.750   1.2323   0.01640   0.00914  -0.0759   0.3127   1.0000
   8.000   1.2526   0.01678   0.00948  -0.0747   0.2847   1.0000
   8.250   1.2704   0.01738   0.00994  -0.0733   0.2466   1.0000
   8.500   1.2853   0.01829   0.01062  -0.0715   0.1985   1.0000
   8.750   1.2943   0.01973   0.01170  -0.0690   0.1426   1.0000
   9.000   1.3034   0.02115   0.01291  -0.0666   0.1116   1.0000
   9.250   1.3109   0.02263   0.01413  -0.0639   0.0636   1.0000
   9.500   1.3125   0.02427   0.01559  -0.0604   0.0415   1.0000
   9.750   1.3188   0.02555   0.01689  -0.0575   0.0336   1.0000
  10.000   1.3257   0.02683   0.01824  -0.0548   0.0305   1.0000
  10.250   1.3328   0.02814   0.01966  -0.0525   0.0287   1.0000
  10.500   1.3377   0.02967   0.02131  -0.0501   0.0273   1.0000
  10.750   1.3399   0.03147   0.02323  -0.0478   0.0264   1.0000
  11.000   1.3387   0.03367   0.02556  -0.0457   0.0256   1.0000
  11.250   1.3368   0.03607   0.02808  -0.0438   0.0251   1.0000
  11.500   1.3371   0.03842   0.03057  -0.0424   0.0245   1.0000
  11.750   1.3367   0.04098   0.03326  -0.0413   0.0239   1.0000
  12.000   1.3357   0.04371   0.03612  -0.0404   0.0234   1.0000
  12.250   1.3340   0.04659   0.03910  -0.0396   0.0229   1.0000
  12.500   1.3324   0.04954   0.04216  -0.0389   0.0225   1.0000
  12.750   1.3311   0.05247   0.04520  -0.0382   0.0222   1.0000
  13.000   1.3306   0.05535   0.04818  -0.0374   0.0220   1.0000
  13.250   1.3312   0.05811   0.05102  -0.0366   0.0217   1.0000
  13.500   1.3332   0.06072   0.05371  -0.0357   0.0215   1.0000
  13.750   1.3367   0.06317   0.05625  -0.0347   0.0213   1.0000
  14.000   1.3417   0.06553   0.05870  -0.0336   0.0212   1.0000
  14.250   1.3469   0.06793   0.06122  -0.0325   0.0211   1.0000
  14.500   1.3518   0.07051   0.06395  -0.0315   0.0211   1.0000
  14.750   1.3549   0.07344   0.06705  -0.0307   0.0211   1.0000
  15.000   1.3554   0.07680   0.07064  -0.0303   0.0213   1.0000
  15.250   1.3528   0.08060   0.07467  -0.0302   0.0214   1.0000
  15.500   1.3474   0.08485   0.07913  -0.0307   0.0214   1.0000
  15.750   1.3397   0.08952   0.08402  -0.0316   0.0214   1.0000
  16.000   1.3299   0.09463   0.08935  -0.0330   0.0215   1.0000
  16.250   1.3171   0.10033   0.09528  -0.0351   0.0215   1.0000
  16.500   1.3007   0.10693   0.10213  -0.0381   0.0217   1.0000
  16.750   1.2793   0.11481   0.11031  -0.0422   0.0220   1.0000
  17.000   1.2578   0.12307   0.11881  -0.0468   0.0223   1.0000
  17.250   1.2345   0.13219   0.12817  -0.0524   0.0227   1.0000
  17.500   1.2104   0.14205   0.13826  -0.0587   0.0231   1.0000
  17.750   1.1853   0.15287   0.14925  -0.0659   0.0236   1.0000
  18.000   1.1595   0.16470   0.16124  -0.0739   0.0242   1.0000
  18.250   1.1362   0.17662   0.17325  -0.0815   0.0249   1.0000
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