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GOE 509 AIRFOIL (goe509-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 509 AIRFOIL (goe509-il)
Reynolds number: 200,000
Max Cl/Cd: 69.27 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe509-il-200000.txt
Download as CSV file: xf-goe509-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 509 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3075   0.10729   0.10392  -0.0313   1.0000   0.0433
  -9.250  -0.3094   0.10491   0.10158  -0.0308   1.0000   0.0442
  -9.000  -0.3136   0.10253   0.09925  -0.0303   1.0000   0.0453
  -8.750  -0.2573   0.09024   0.08734  -0.0411   0.9922   0.0488
  -8.500  -0.2274   0.08638   0.08346  -0.0400   0.9895   0.0505
  -8.250  -0.2118   0.08207   0.07913  -0.0431   0.9860   0.0524
  -8.000  -0.2003   0.07747   0.07453  -0.0474   0.9824   0.0543
  -7.750  -0.3321   0.08711   0.08409  -0.0406   0.9876   0.0497
  -7.500  -0.3077   0.08358   0.08055  -0.0435   0.9840   0.0513
  -7.250  -0.2882   0.07938   0.07632  -0.0489   0.9757   0.0532
  -7.000  -0.2661   0.07405   0.07090  -0.0581   0.9660   0.0568
  -6.750  -0.2434   0.06560   0.06223  -0.0708   0.9579   0.0592
  -6.500  -0.2292   0.06298   0.05963  -0.0698   0.9491   0.0602
  -6.250  -0.2022   0.06012   0.05675  -0.0719   0.9454   0.0625
  -6.000  -0.1813   0.05631   0.05276  -0.0756   0.9347   0.0690
  -5.750  -0.1583   0.05003   0.04624  -0.0803   0.9298   0.0725
  -5.500  -0.1433   0.04843   0.04466  -0.0788   0.9197   0.0745
  -5.250  -0.1132   0.04518   0.04126  -0.0814   0.9157   0.0799
  -5.000  -0.1036   0.04041   0.03608  -0.0808   0.9042   0.0867
  -4.750  -0.0717   0.03842   0.03409  -0.0823   0.9010   0.0906
  -4.500  -0.0591   0.03536   0.03064  -0.0806   0.8903   0.1019
  -4.250  -0.0428   0.02563   0.01915  -0.0760   0.8855   0.0586
  -4.000  -0.0262   0.02273   0.01595  -0.0740   0.8756   0.0600
  -3.750   0.0104   0.02116   0.01429  -0.0756   0.8715   0.0633
  -3.500   0.0362   0.01983   0.01270  -0.0746   0.8627   0.0650
  -3.250   0.0735   0.01875   0.01133  -0.0759   0.8575   0.0689
  -3.000   0.1041   0.01784   0.01017  -0.0759   0.8492   0.0708
  -2.750   0.1414   0.01633   0.00860  -0.0776   0.8428   0.0754
  -2.500   0.1731   0.01567   0.00787  -0.0780   0.8336   0.0798
  -2.250   0.2107   0.01503   0.00707  -0.0795   0.8256   0.0840
  -2.000   0.2379   0.01423   0.00632  -0.0792   0.8143   0.0906
  -1.750   0.2674   0.01381   0.00584  -0.0791   0.8035   0.0978
  -1.500   0.2966   0.01327   0.00531  -0.0791   0.7931   0.1090
  -1.250   0.3185   0.01292   0.00500  -0.0776   0.7805   0.1265
  -1.000   0.3392   0.01232   0.00487  -0.0760   0.7683   0.2238
  -0.750   0.3634   0.01232   0.00496  -0.0749   0.7555   0.3213
  -0.500   0.3872   0.01225   0.00487  -0.0737   0.7418   0.3542
  -0.250   0.4099   0.01213   0.00474  -0.0724   0.7267   0.3811
   0.000   0.4305   0.01195   0.00460  -0.0706   0.7099   0.4069
   0.250   0.4489   0.01172   0.00445  -0.0684   0.6915   0.4406
   0.500   0.6612   0.01121   0.00489  -0.1066   0.6412   0.9980
   0.750   0.6880   0.01132   0.00476  -0.1063   0.6131   1.0000
   1.000   0.7070   0.01149   0.00474  -0.1044   0.5883   1.0000
   1.250   0.7262   0.01169   0.00473  -0.1026   0.5670   1.0000
   1.500   0.7457   0.01188   0.00476  -0.1009   0.5486   1.0000
   1.750   0.7660   0.01208   0.00481  -0.0994   0.5344   1.0000
   2.000   0.7865   0.01230   0.00488  -0.0980   0.5226   1.0000
   2.250   0.8072   0.01249   0.00498  -0.0965   0.5111   1.0000
   2.500   0.8281   0.01271   0.00509  -0.0952   0.5014   1.0000
   2.750   0.8491   0.01295   0.00522  -0.0939   0.4923   1.0000
   3.000   0.8703   0.01316   0.00538  -0.0926   0.4835   1.0000
   3.250   0.8920   0.01343   0.00553  -0.0914   0.4760   1.0000
   3.500   0.9136   0.01364   0.00573  -0.0902   0.4689   1.0000
   3.750   0.9354   0.01391   0.00594  -0.0891   0.4620   1.0000
   4.000   0.9576   0.01418   0.00617  -0.0880   0.4558   1.0000
   4.250   0.9790   0.01442   0.00641  -0.0868   0.4491   1.0000
   4.500   1.0026   0.01477   0.00665  -0.0861   0.4433   1.0000
   4.750   1.0230   0.01499   0.00696  -0.0847   0.4370   1.0000
   5.000   1.0446   0.01527   0.00722  -0.0835   0.4307   1.0000
   5.250   1.0671   0.01561   0.00753  -0.0826   0.4247   1.0000
   5.500   1.0863   0.01584   0.00783  -0.0809   0.4172   1.0000
   5.750   1.1078   0.01618   0.00811  -0.0798   0.4094   1.0000
   6.000   1.1249   0.01637   0.00840  -0.0777   0.4010   1.0000
   6.250   1.1450   0.01668   0.00865  -0.0763   0.3930   1.0000
   6.500   1.1603   0.01684   0.00893  -0.0739   0.3835   1.0000
   6.750   1.1772   0.01707   0.00917  -0.0718   0.3744   1.0000
   7.000   1.1920   0.01723   0.00938  -0.0694   0.3644   1.0000
   7.250   1.2066   0.01742   0.00964  -0.0668   0.3540   1.0000
   7.500   1.2208   0.01763   0.00987  -0.0643   0.3440   1.0000
   7.750   1.2341   0.01784   0.01014  -0.0615   0.3327   1.0000
   8.000   1.2469   0.01807   0.01044  -0.0587   0.3204   1.0000
   8.250   1.2580   0.01835   0.01074  -0.0556   0.3071   1.0000
   8.500   1.2664   0.01866   0.01105  -0.0521   0.2939   1.0000
   8.750   1.2733   0.01902   0.01140  -0.0483   0.2812   1.0000
   9.000   1.2806   0.01947   0.01181  -0.0447   0.2696   1.0000
   9.250   1.2890   0.01997   0.01229  -0.0415   0.2580   1.0000
   9.500   1.2987   0.02050   0.01284  -0.0386   0.2474   1.0000
   9.750   1.3079   0.02111   0.01345  -0.0357   0.2380   1.0000
  10.000   1.3164   0.02177   0.01410  -0.0328   0.2288   1.0000
  10.250   1.3271   0.02239   0.01478  -0.0304   0.2201   1.0000
  10.500   1.3346   0.02318   0.01554  -0.0276   0.2121   1.0000
  10.750   1.3451   0.02387   0.01632  -0.0254   0.2033   1.0000
  11.000   1.3528   0.02472   0.01721  -0.0229   0.1948   1.0000
  11.250   1.3584   0.02571   0.01821  -0.0203   0.1848   1.0000
  11.500   1.3660   0.02666   0.01923  -0.0180   0.1739   1.0000
  11.750   1.3710   0.02783   0.02044  -0.0157   0.1608   1.0000
  12.000   1.3746   0.02917   0.02179  -0.0134   0.1439   1.0000
  12.250   1.3716   0.03111   0.02357  -0.0110   0.1009   1.0000
  12.500   1.3561   0.03418   0.02638  -0.0081   0.0767   1.0000
  12.750   1.3458   0.03709   0.02927  -0.0058   0.0606   1.0000
  13.000   1.3387   0.03987   0.03206  -0.0042   0.0530   1.0000
  13.250   1.3322   0.04276   0.03500  -0.0029   0.0491   1.0000
  13.500   1.3253   0.04585   0.03819  -0.0019   0.0467   1.0000
  13.750   1.3160   0.04938   0.04181  -0.0012   0.0449   1.0000
  14.000   1.3050   0.05328   0.04583  -0.0009   0.0436   1.0000
  14.250   1.2927   0.05755   0.05023  -0.0010   0.0427   1.0000
  14.500   1.2827   0.06176   0.05458  -0.0013   0.0418   1.0000
  14.750   1.2723   0.06616   0.05913  -0.0018   0.0410   1.0000
  15.000   1.2614   0.07078   0.06387  -0.0026   0.0400   1.0000
  15.250   1.2526   0.07515   0.06836  -0.0034   0.0396   1.0000
  15.500   1.2430   0.07967   0.07296  -0.0042   0.0386   1.0000
  15.750   1.2338   0.08404   0.07738  -0.0049   0.0376   1.0000
  16.000   1.2278   0.08780   0.08115  -0.0053   0.0365   1.0000
  16.250   1.2287   0.09005   0.08337  -0.0045   0.0355   1.0000
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