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GOE 359 AIRFOIL (goe359-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 359 AIRFOIL (goe359-il)
Reynolds number: 200,000
Max Cl/Cd: 83.4 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe359-il-200000.txt
Download as CSV file: xf-goe359-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 359 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2807   0.10880   0.10548  -0.0301   1.0000   0.0268
  -8.250  -0.2817   0.10692   0.10366  -0.0305   1.0000   0.0269
  -8.000  -0.2843   0.10508   0.10190  -0.0304   1.0000   0.0269
  -7.750  -0.2839   0.10285   0.09975  -0.0312   1.0000   0.0269
  -7.500  -0.2835   0.10063   0.09760  -0.0320   1.0000   0.0270
  -7.250  -0.1930   0.08028   0.07754  -0.0299   0.9943   0.0296
  -6.500  -0.2622   0.08557   0.08271  -0.0282   0.9938   0.0292
  -6.250  -0.2318   0.08115   0.07827  -0.0353   0.9866   0.0311
  -6.000  -0.1978   0.07651   0.07359  -0.0441   0.9778   0.0332
  -5.750  -0.1398   0.07185   0.06881  -0.0625   0.9661   0.0356
  -5.500  -0.0861   0.06680   0.06359  -0.0762   0.9585   0.0360
  -5.250  -0.0671   0.06026   0.05706  -0.0791   0.9493   0.0369
  -5.000  -0.0435   0.05647   0.05327  -0.0807   0.9420   0.0383
  -4.750  -0.0096   0.05286   0.04959  -0.0856   0.9326   0.0411
  -4.500   0.0601   0.04885   0.04512  -0.0997   0.9212   0.0472
  -4.250   0.0848   0.04316   0.03941  -0.1030   0.9104   0.0487
  -4.000   0.1116   0.04048   0.03667  -0.1047   0.8984   0.0512
  -3.500   0.1781   0.03449   0.03021  -0.1109   0.8710   0.0632
  -3.250   0.2136   0.03191   0.02717  -0.1136   0.8571   0.0738
  -3.000   0.2344   0.03025   0.02553  -0.1132   0.8428   0.0777
  -2.750   0.2631   0.02835   0.02333  -0.1141   0.8292   0.0889
  -2.500   0.2897   0.02692   0.02170  -0.1145   0.8156   0.1024
  -2.250   0.3165   0.02555   0.02010  -0.1147   0.8023   0.1161
  -2.000   0.3428   0.02424   0.01861  -0.1148   0.7891   0.1304
  -1.750   0.3684   0.02300   0.01723  -0.1147   0.7760   0.1460
  -1.500   0.3954   0.02233   0.01632  -0.1146   0.7631   0.1727
  -1.000   0.4648   0.01673   0.00934  -0.1138   0.7416   0.0797
  -0.750   0.4937   0.01583   0.00800  -0.1131   0.7291   0.0720
  -0.500   0.5208   0.01493   0.00693  -0.1126   0.7164   0.0707
  -0.250   0.5477   0.01442   0.00625  -0.1120   0.7031   0.0713
   0.000   0.5745   0.01404   0.00574  -0.1115   0.6900   0.0723
   0.250   0.6011   0.01359   0.00521  -0.1109   0.6774   0.0721
   0.500   0.6277   0.01327   0.00481  -0.1104   0.6654   0.0724
   0.750   0.6543   0.01299   0.00448  -0.1100   0.6537   0.0738
   1.000   0.6808   0.01282   0.00430  -0.1096   0.6414   0.0771
   1.250   0.7075   0.01278   0.00421  -0.1092   0.6295   0.0826
   1.500   0.7342   0.01275   0.00417  -0.1088   0.6181   0.0980
   1.750   0.7537   0.01125   0.00431  -0.1073   0.6080   0.7704
   2.000   0.7866   0.01114   0.00423  -0.1080   0.5965   1.0000
   2.250   0.8132   0.01132   0.00430  -0.1076   0.5864   1.0000
   2.500   0.8399   0.01153   0.00438  -0.1073   0.5778   1.0000
   2.750   0.8664   0.01172   0.00448  -0.1070   0.5686   1.0000
   3.000   0.8928   0.01192   0.00462  -0.1066   0.5597   1.0000
   3.250   0.9191   0.01212   0.00473  -0.1063   0.5504   1.0000
   3.500   0.9448   0.01227   0.00485  -0.1058   0.5390   1.0000
   3.750   0.9704   0.01243   0.00498  -0.1053   0.5274   1.0000
   4.000   0.9960   0.01261   0.00511  -0.1048   0.5165   1.0000
   4.250   1.0217   0.01281   0.00527  -0.1044   0.5065   1.0000
   4.500   1.0473   0.01300   0.00547  -0.1039   0.4960   1.0000
   4.750   1.0725   0.01318   0.00566  -0.1034   0.4843   1.0000
   5.000   1.0971   0.01337   0.00583  -0.1028   0.4707   1.0000
   5.250   1.1207   0.01355   0.00596  -0.1020   0.4521   1.0000
   5.500   1.1437   0.01374   0.00612  -0.1011   0.4304   1.0000
   5.750   1.1668   0.01399   0.00631  -0.1002   0.4094   1.0000
   6.000   1.1901   0.01427   0.00656  -0.0995   0.3909   1.0000
   6.250   1.2121   0.01458   0.00683  -0.0985   0.3595   1.0000
   6.500   1.2326   0.01504   0.00712  -0.0974   0.3187   1.0000
   6.750   1.2519   0.01569   0.00754  -0.0962   0.2795   1.0000
   7.000   1.2709   0.01641   0.00808  -0.0950   0.2506   1.0000
   7.250   1.2905   0.01711   0.00867  -0.0939   0.2272   1.0000
   7.500   1.3094   0.01785   0.00932  -0.0927   0.2031   1.0000
   7.750   1.3280   0.01861   0.00995  -0.0914   0.1704   1.0000
   8.000   1.3419   0.01977   0.01078  -0.0896   0.1232   1.0000
   8.250   1.3506   0.02138   0.01201  -0.0872   0.0655   1.0000
   8.500   1.3649   0.02244   0.01301  -0.0853   0.0530   1.0000
   8.750   1.3806   0.02332   0.01396  -0.0836   0.0423   1.0000
   9.000   1.3898   0.02467   0.01524  -0.0811   0.0247   1.0000
   9.250   1.4005   0.02573   0.01638  -0.0787   0.0227   1.0000
   9.500   1.4108   0.02676   0.01755  -0.0763   0.0218   1.0000
   9.750   1.4198   0.02791   0.01887  -0.0738   0.0212   1.0000
  10.000   1.4265   0.02926   0.02040  -0.0713   0.0208   1.0000
  10.250   1.4308   0.03084   0.02218  -0.0689   0.0205   1.0000
  10.500   1.4325   0.03273   0.02426  -0.0666   0.0203   1.0000
  10.750   1.4322   0.03495   0.02665  -0.0647   0.0202   1.0000
  11.000   1.4303   0.03748   0.02938  -0.0631   0.0202   1.0000
  11.250   1.4270   0.04033   0.03239  -0.0618   0.0202   1.0000
  11.500   1.4228   0.04344   0.03565  -0.0608   0.0201   1.0000
  11.750   1.4185   0.04668   0.03903  -0.0601   0.0200   1.0000
  12.000   1.4142   0.05003   0.04251  -0.0595   0.0198   1.0000
  12.250   1.4099   0.05342   0.04603  -0.0590   0.0196   1.0000
  12.500   1.4062   0.05679   0.04951  -0.0584   0.0194   1.0000
  12.750   1.4033   0.06005   0.05289  -0.0578   0.0192   1.0000
  13.000   1.4018   0.06310   0.05604  -0.0570   0.0193   1.0000
  13.250   1.4027   0.06583   0.05886  -0.0559   0.0194   1.0000
  13.500   1.4062   0.06821   0.06133  -0.0543   0.0195   1.0000
  13.750   1.4128   0.07026   0.06348  -0.0524   0.0198   1.0000
  14.000   1.4291   0.07145   0.06473  -0.0489   0.0202   1.0000
  14.250   1.4371   0.07366   0.06706  -0.0481   0.0206   1.0000
  14.500   1.4405   0.07640   0.06999  -0.0479   0.0211   1.0000
  14.750   1.4442   0.07958   0.07353  -0.0470   0.0223   1.0000
  15.000   1.4441   0.08394   0.07828  -0.0455   0.0241   1.0000
  15.250   1.4413   0.08871   0.08330  -0.0446   0.0254   1.0000
  15.500   1.1903   0.09371   0.08837  -0.0349   0.0206   1.0000
  15.750   1.1817   0.09653   0.09135  -0.0350   0.0209   1.0000
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