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GOE 398 AIRFOIL (goe398-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 398 AIRFOIL (goe398-il)
Reynolds number: 200,000
Max Cl/Cd: 71.26 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe398-il-200000.txt
Download as CSV file: xf-goe398-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 398 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2981   0.11009   0.10657  -0.0414   1.0000   0.0675
 -10.250  -0.3410   0.10814   0.10476  -0.0423   1.0000   0.0686
 -10.000  -0.3670   0.10532   0.10204  -0.0427   0.9992   0.0689
  -9.750  -0.3352   0.10236   0.09905  -0.0404   0.9978   0.0699
  -9.500  -0.3065   0.09985   0.09653  -0.0414   0.9952   0.0720
  -9.250  -0.2901   0.09568   0.09235  -0.0467   0.9907   0.0755
  -9.000  -0.3051   0.08584   0.08255  -0.0641   0.9809   0.0790
  -8.750  -0.2752   0.08400   0.08069  -0.0620   0.9779   0.0802
  -8.500  -0.2514   0.08108   0.07775  -0.0644   0.9735   0.0820
  -8.250  -0.2369   0.07688   0.07355  -0.0701   0.9666   0.0854
  -8.000  -0.2620   0.06374   0.06024  -0.0914   0.9471   0.0905
  -7.750  -0.3036   0.04427   0.03970  -0.1000   0.9314   0.0694
  -7.500  -0.2977   0.03431   0.02869  -0.1017   0.9265   0.0601
  -7.250  -0.2855   0.03164   0.02563  -0.1000   0.9166   0.0602
  -7.000  -0.2582   0.02874   0.02246  -0.1012   0.9127   0.0615
  -6.750  -0.2217   0.02722   0.02090  -0.1034   0.9102   0.0631
  -6.500  -0.2038   0.02575   0.01918  -0.1017   0.9006   0.0639
  -6.250  -0.1715   0.02397   0.01709  -0.1026   0.8957   0.0651
  -6.000  -0.1401   0.02267   0.01547  -0.1031   0.8901   0.0674
  -5.750  -0.1162   0.02183   0.01430  -0.1019   0.8811   0.0688
  -5.500  -0.0810   0.02011   0.01252  -0.1033   0.8763   0.0708
  -5.250  -0.0581   0.01942   0.01179  -0.1021   0.8664   0.0728
  -5.000  -0.0257   0.01866   0.01089  -0.1026   0.8599   0.0761
  -4.750  -0.0007   0.01807   0.01015  -0.1017   0.8515   0.0789
  -4.500   0.0268   0.01720   0.00934  -0.1014   0.8444   0.0825
  -4.250   0.0566   0.01665   0.00872  -0.1015   0.8384   0.0870
  -4.000   0.0781   0.01611   0.00820  -0.1000   0.8295   0.0924
  -3.750   0.1078   0.01564   0.00768  -0.1000   0.8236   0.1006
  -3.500   0.1285   0.01518   0.00731  -0.0985   0.8153   0.1099
  -3.250   0.1544   0.01474   0.00690  -0.0978   0.8082   0.1249
  -3.000   0.1797   0.01440   0.00660  -0.0971   0.8012   0.1461
  -2.750   0.2027   0.01413   0.00646  -0.0959   0.7929   0.1737
  -2.500   0.2315   0.01382   0.00619  -0.0958   0.7871   0.2128
  -2.250   0.2511   0.01358   0.00610  -0.0941   0.7783   0.2481
  -2.000   0.2765   0.01320   0.00589  -0.0934   0.7714   0.2931
  -1.750   0.2971   0.01288   0.00585  -0.0919   0.7632   0.3612
  -1.500   0.3171   0.01241   0.00578  -0.0901   0.7553   0.4763
  -1.250   0.3356   0.01194   0.00577  -0.0878   0.7481   0.6093
  -1.000   0.3780   0.01125   0.00581  -0.0898   0.7397   0.8294
  -0.750   0.5030   0.01122   0.00569  -0.1089   0.7317   0.9635
  -0.500   0.5796   0.01127   0.00559  -0.1187   0.7211   1.0000
  -0.250   0.6003   0.01128   0.00547  -0.1172   0.7115   1.0000
   0.000   0.6216   0.01128   0.00535  -0.1158   0.7012   1.0000
   0.250   0.6416   0.01133   0.00532  -0.1141   0.6901   1.0000
   0.500   0.6645   0.01137   0.00521  -0.1129   0.6798   1.0000
   0.750   0.6847   0.01142   0.00519  -0.1112   0.6674   1.0000
   1.000   0.7054   0.01150   0.00517  -0.1096   0.6546   1.0000
   1.250   0.7271   0.01158   0.00514  -0.1081   0.6419   1.0000
   1.500   0.7492   0.01167   0.00509  -0.1067   0.6288   1.0000
   1.750   0.7691   0.01178   0.00512  -0.1050   0.6142   1.0000
   2.000   0.7893   0.01191   0.00517  -0.1033   0.5996   1.0000
   2.250   0.8098   0.01205   0.00523  -0.1016   0.5854   1.0000
   2.500   0.8307   0.01221   0.00529  -0.1001   0.5719   1.0000
   2.750   0.8518   0.01238   0.00535  -0.0986   0.5587   1.0000
   3.000   0.8722   0.01256   0.00546  -0.0970   0.5454   1.0000
   3.250   0.8925   0.01276   0.00560  -0.0954   0.5324   1.0000
   3.500   0.9133   0.01297   0.00573  -0.0939   0.5207   1.0000
   3.750   0.9347   0.01322   0.00586  -0.0926   0.5101   1.0000
   4.000   0.9547   0.01344   0.00606  -0.0910   0.4983   1.0000
   4.250   0.9755   0.01371   0.00626  -0.0895   0.4879   1.0000
   4.500   0.9966   0.01400   0.00645  -0.0882   0.4778   1.0000
   4.750   1.0169   0.01427   0.00672  -0.0867   0.4679   1.0000
   5.000   1.0390   0.01462   0.00694  -0.0856   0.4590   1.0000
   5.250   1.0584   0.01490   0.00725  -0.0840   0.4493   1.0000
   5.500   1.0802   0.01526   0.00753  -0.0828   0.4405   1.0000
   5.750   1.0992   0.01556   0.00785  -0.0811   0.4309   1.0000
   6.000   1.1200   0.01594   0.00817  -0.0799   0.4219   1.0000
   6.250   1.1388   0.01626   0.00850  -0.0782   0.4125   1.0000
   6.500   1.1586   0.01665   0.00886  -0.0767   0.4037   1.0000
   6.750   1.1770   0.01699   0.00919  -0.0750   0.3946   1.0000
   7.000   1.1957   0.01738   0.00959  -0.0734   0.3858   1.0000
   7.250   1.2135   0.01774   0.00994  -0.0716   0.3770   1.0000
   7.500   1.2303   0.01812   0.01034  -0.0696   0.3680   1.0000
   7.750   1.2465   0.01848   0.01066  -0.0676   0.3588   1.0000
   8.000   1.2591   0.01883   0.01107  -0.0649   0.3489   1.0000
   8.250   1.2733   0.01922   0.01138  -0.0625   0.3397   1.0000
   8.500   1.2809   0.01953   0.01178  -0.0589   0.3303   1.0000
   8.750   1.2937   0.01997   0.01216  -0.0564   0.3221   1.0000
   9.000   1.3043   0.02036   0.01264  -0.0535   0.3137   1.0000
   9.250   1.3177   0.02086   0.01308  -0.0513   0.3062   1.0000
   9.500   1.3287   0.02133   0.01363  -0.0487   0.2982   1.0000
   9.750   1.3436   0.02190   0.01412  -0.0469   0.2916   1.0000
  10.000   1.3552   0.02243   0.01479  -0.0446   0.2846   1.0000
  10.250   1.3678   0.02303   0.01534  -0.0425   0.2779   1.0000
  10.500   1.3795   0.02366   0.01605  -0.0405   0.2712   1.0000
  10.750   1.3905   0.02431   0.01674  -0.0384   0.2646   1.0000
  11.000   1.4034   0.02503   0.01746  -0.0366   0.2586   1.0000
  11.250   1.4133   0.02577   0.01832  -0.0346   0.2524   1.0000
  11.500   1.4239   0.02658   0.01908  -0.0328   0.2461   1.0000
  11.750   1.4331   0.02743   0.02007  -0.0309   0.2401   1.0000
  12.000   1.4403   0.02839   0.02108  -0.0289   0.2333   1.0000
  12.250   1.4489   0.02939   0.02212  -0.0272   0.2273   1.0000
  12.500   1.4556   0.03049   0.02335  -0.0255   0.2206   1.0000
  12.750   1.4619   0.03170   0.02453  -0.0238   0.2142   1.0000
  13.000   1.4666   0.03303   0.02606  -0.0222   0.2068   1.0000
  13.250   1.4683   0.03463   0.02766  -0.0206   0.1989   1.0000
  13.500   1.4697   0.03636   0.02954  -0.0192   0.1892   1.0000
  13.750   1.4686   0.03841   0.03167  -0.0179   0.1780   1.0000
  14.000   1.4645   0.04088   0.03418  -0.0167   0.1644   1.0000
  14.250   1.4554   0.04397   0.03727  -0.0157   0.1470   1.0000
  14.500   1.4438   0.04754   0.04080  -0.0149   0.1278   1.0000
  14.750   1.4291   0.05163   0.04481  -0.0143   0.1114   1.0000
  15.000   1.4151   0.05583   0.04898  -0.0140   0.1017   1.0000
  15.250   1.4004   0.06029   0.05343  -0.0140   0.0953   1.0000
  15.500   1.3896   0.06442   0.05760  -0.0141   0.0907   1.0000
  15.750   1.3766   0.06894   0.06213  -0.0145   0.0873   1.0000
  16.000   1.3687   0.07292   0.06617  -0.0148   0.0845   1.0000
  16.250   1.3622   0.07677   0.07010  -0.0152   0.0817   1.0000
  16.500   1.3553   0.08070   0.07406  -0.0157   0.0793   1.0000
  16.750   1.3493   0.08431   0.07761  -0.0159   0.0768   1.0000
  17.000   1.3484   0.08747   0.08087  -0.0163   0.0749   1.0000
  17.250   1.3475   0.09065   0.08413  -0.0167   0.0728   1.0000
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