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GOE 363 AIRFOIL (goe363-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 363 AIRFOIL (goe363-il)
Reynolds number: 200,000
Max Cl/Cd: 70.1 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe363-il-200000.txt
Download as CSV file: xf-goe363-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 363 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2769   0.11524   0.11199  -0.0371   1.0000   0.0407
  -9.500  -0.2948   0.11481   0.11165  -0.0340   1.0000   0.0407
  -9.250  -0.3143   0.11448   0.11141  -0.0307   1.0000   0.0408
  -9.000  -0.2956   0.10931   0.10624  -0.0267   1.0000   0.0420
  -8.750  -0.2902   0.10713   0.10409  -0.0258   0.9990   0.0430
  -8.500  -0.2719   0.10341   0.10036  -0.0296   0.9959   0.0448
  -8.250  -0.2558   0.09950   0.09645  -0.0344   0.9923   0.0469
  -8.000  -0.2477   0.09556   0.09253  -0.0465   0.9842   0.0496
  -7.750  -0.2343   0.08981   0.08679  -0.0575   0.9746   0.0503
  -7.500  -0.2164   0.08632   0.08329  -0.0532   0.9740   0.0515
  -7.250  -0.1902   0.08295   0.07990  -0.0557   0.9715   0.0536
  -7.000  -0.1710   0.07930   0.07625  -0.0608   0.9643   0.0565
  -6.750  -0.1393   0.07106   0.06793  -0.0820   0.9567   0.0615
  -6.500  -0.1163   0.06918   0.06607  -0.0792   0.9559   0.0638
  -6.250  -0.1017   0.06662   0.06351  -0.0809   0.9473   0.0667
  -6.000  -0.0618   0.05884   0.05553  -0.0981   0.9419   0.0738
  -5.750  -0.0470   0.05715   0.05387  -0.0962   0.9357   0.0756
  -5.500  -0.0215   0.05442   0.05109  -0.0990   0.9304   0.0801
  -5.250   0.0142   0.04924   0.04573  -0.1072   0.9266   0.0881
  -5.000   0.0320   0.04753   0.04400  -0.1069   0.9187   0.0925
  -4.750   0.0717   0.02992   0.02471  -0.1193   0.9123   0.0607
  -4.500   0.0960   0.02629   0.02070  -0.1198   0.9062   0.0601
  -4.250   0.1243   0.02330   0.01727  -0.1202   0.9000   0.0595
  -4.000   0.1594   0.02101   0.01451  -0.1212   0.8959   0.0597
  -3.750   0.1847   0.01973   0.01291  -0.1203   0.8866   0.0612
  -3.500   0.2177   0.01795   0.01093  -0.1206   0.8806   0.0628
  -3.250   0.2432   0.01701   0.00990  -0.1196   0.8702   0.0642
  -3.000   0.2728   0.01614   0.00893  -0.1191   0.8624   0.0665
  -2.750   0.2998   0.01551   0.00821  -0.1182   0.8525   0.0699
  -2.500   0.3267   0.01492   0.00751  -0.1173   0.8422   0.0724
  -2.250   0.3553   0.01413   0.00672  -0.1168   0.8336   0.0768
  -2.000   0.3809   0.01376   0.00633  -0.1158   0.8222   0.0830
  -1.750   0.4080   0.01339   0.00601  -0.1152   0.8125   0.0969
  -1.500   0.4364   0.01312   0.00584  -0.1147   0.8031   0.1459
  -1.250   0.4625   0.01302   0.00574  -0.1140   0.7910   0.1777
  -1.000   0.4891   0.01288   0.00558  -0.1134   0.7792   0.1961
  -0.750   0.5160   0.01274   0.00542  -0.1128   0.7669   0.2153
  -0.500   0.5427   0.01257   0.00524  -0.1122   0.7534   0.2320
  -0.250   0.5690   0.01239   0.00506  -0.1116   0.7382   0.2486
   0.000   0.5950   0.01220   0.00492  -0.1109   0.7208   0.2714
   0.250   0.6207   0.01196   0.00476  -0.1103   0.7017   0.3057
   0.500   0.6447   0.01131   0.00459  -0.1094   0.6814   0.4476
   0.750   0.6748   0.01018   0.00442  -0.1089   0.6578   1.0000
   1.000   0.7002   0.01031   0.00428  -0.1080   0.6326   1.0000
   1.250   0.7250   0.01050   0.00423  -0.1072   0.6058   1.0000
   1.500   0.7495   0.01075   0.00423  -0.1063   0.5800   1.0000
   1.750   0.7737   0.01107   0.00429  -0.1054   0.5558   1.0000
   2.000   0.7977   0.01138   0.00441  -0.1045   0.5314   1.0000
   2.250   0.8213   0.01174   0.00456  -0.1036   0.5064   1.0000
   2.500   0.8444   0.01210   0.00473  -0.1027   0.4787   1.0000
   2.750   0.8670   0.01247   0.00491  -0.1017   0.4474   1.0000
   3.000   0.8891   0.01288   0.00511  -0.1006   0.4151   1.0000
   3.250   0.9112   0.01332   0.00534  -0.0996   0.3877   1.0000
   3.500   0.9335   0.01380   0.00561  -0.0987   0.3681   1.0000
   3.750   0.9563   0.01427   0.00591  -0.0979   0.3537   1.0000
   4.000   0.9799   0.01470   0.00624  -0.0972   0.3421   1.0000
   4.250   1.0039   0.01512   0.00658  -0.0966   0.3327   1.0000
   4.500   1.0272   0.01561   0.00692  -0.0959   0.3245   1.0000
   4.750   1.0518   0.01597   0.00728  -0.0954   0.3168   1.0000
   5.000   1.0757   0.01643   0.00763  -0.0948   0.3104   1.0000
   5.250   1.1001   0.01683   0.00801  -0.0943   0.3043   1.0000
   5.500   1.1243   0.01721   0.00838  -0.0938   0.2985   1.0000
   5.750   1.1484   0.01775   0.00881  -0.0933   0.2934   1.0000
   6.000   1.1728   0.01809   0.00922  -0.0928   0.2887   1.0000
   6.250   1.1969   0.01848   0.00962  -0.0923   0.2839   1.0000
   6.500   1.2209   0.01897   0.01006  -0.0918   0.2795   1.0000
   6.750   1.2449   0.01943   0.01055  -0.0913   0.2751   1.0000
   7.000   1.2682   0.01981   0.01100  -0.0907   0.2704   1.0000
   7.250   1.2913   0.02025   0.01146  -0.0901   0.2658   1.0000
   7.500   1.3148   0.02081   0.01199  -0.0896   0.2611   1.0000
   7.750   1.3351   0.02112   0.01242  -0.0885   0.2547   1.0000
   8.000   1.3554   0.02162   0.01284  -0.0876   0.2478   1.0000
   8.250   1.3737   0.02193   0.01331  -0.0862   0.2406   1.0000
   8.500   1.3923   0.02237   0.01374  -0.0849   0.2342   1.0000
   8.750   1.4096   0.02279   0.01426  -0.0835   0.2271   1.0000
   9.000   1.4245   0.02319   0.01469  -0.0816   0.2201   1.0000
   9.250   1.4397   0.02369   0.01527  -0.0799   0.2135   1.0000
   9.500   1.4538   0.02415   0.01581  -0.0781   0.2062   1.0000
   9.750   1.4677   0.02471   0.01642  -0.0763   0.1991   1.0000
  10.000   1.4821   0.02525   0.01705  -0.0747   0.1917   1.0000
  10.250   1.4961   0.02588   0.01775  -0.0731   0.1843   1.0000
  10.500   1.5085   0.02655   0.01846  -0.0715   0.1748   1.0000
  10.750   1.5230   0.02722   0.01920  -0.0702   0.1634   1.0000
  11.000   1.5350   0.02811   0.02009  -0.0688   0.1516   1.0000
  11.250   1.5451   0.02921   0.02117  -0.0672   0.1417   1.0000
  11.500   1.5519   0.03061   0.02253  -0.0655   0.1312   1.0000
  11.750   1.5565   0.03225   0.02415  -0.0637   0.1224   1.0000
  12.000   1.5618   0.03391   0.02584  -0.0621   0.1134   1.0000
  12.250   1.5677   0.03558   0.02756  -0.0606   0.1045   1.0000
  12.500   1.5725   0.03741   0.02942  -0.0592   0.0918   1.0000
  12.750   1.5591   0.04096   0.03271  -0.0572   0.0498   1.0000
  13.000   1.5394   0.04535   0.03706  -0.0554   0.0322   1.0000
  13.250   1.5307   0.04884   0.04064  -0.0543   0.0280   1.0000
  13.500   1.5254   0.05215   0.04408  -0.0536   0.0265   1.0000
  13.750   1.5197   0.05568   0.04776  -0.0533   0.0254   1.0000
  14.000   1.5125   0.05956   0.05183  -0.0532   0.0247   1.0000
  14.250   1.5037   0.06389   0.05633  -0.0536   0.0241   1.0000
  14.500   1.4929   0.06870   0.06133  -0.0543   0.0237   1.0000
  14.750   1.4802   0.07399   0.06681  -0.0555   0.0233   1.0000
  15.000   1.4651   0.07985   0.07286  -0.0570   0.0230   1.0000
  15.250   1.4480   0.08619   0.07941  -0.0589   0.0229   1.0000
  15.500   1.4293   0.09295   0.08636  -0.0611   0.0228   1.0000
  15.750   1.4097   0.10007   0.09367  -0.0636   0.0227   1.0000
  16.000   1.3888   0.10761   0.10140  -0.0664   0.0227   1.0000
  16.250   1.3683   0.11525   0.10922  -0.0695   0.0228   1.0000
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