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GOE 285 AIRFOIL (goe285-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 285 AIRFOIL (goe285-il)
Reynolds number: 200,000
Max Cl/Cd: 65.15 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe285-il-200000.txt
Download as CSV file: xf-goe285-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 285 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3529   0.08797   0.08435  -0.0340   1.0000   0.0732
  -8.000  -0.3616   0.08525   0.08170  -0.0342   1.0000   0.0748
  -7.750  -0.3868   0.08293   0.07950  -0.0338   1.0000   0.0761
  -7.500  -0.4381   0.07910   0.07568  -0.0386   1.0000   0.0776
  -7.250  -0.4694   0.07593   0.07234  -0.0385   1.0000   0.0779
  -7.000  -0.4491   0.07150   0.06810  -0.0374   0.9983   0.0787
  -6.750  -0.4223   0.06907   0.06572  -0.0379   0.9952   0.0798
  -6.500  -0.3940   0.06584   0.06246  -0.0413   0.9906   0.0816
  -6.250  -0.3625   0.06116   0.05766  -0.0480   0.9847   0.0847
  -6.000  -0.3346   0.05235   0.04832  -0.0594   0.9750   0.0909
  -5.750  -0.2996   0.04928   0.04526  -0.0627   0.9713   0.0923
  -5.500  -0.2819   0.03476   0.02944  -0.0677   0.9610   0.0689
  -5.250  -0.2446   0.03041   0.02472  -0.0709   0.9575   0.0645
  -5.000  -0.2177   0.02515   0.01864  -0.0716   0.9487   0.0613
  -4.750  -0.1771   0.02261   0.01566  -0.0742   0.9447   0.0614
  -4.500  -0.1412   0.02117   0.01401  -0.0757   0.9382   0.0625
  -4.250  -0.1056   0.02003   0.01269  -0.0771   0.9314   0.0646
  -4.000  -0.0666   0.01878   0.01119  -0.0789   0.9271   0.0664
  -3.750  -0.0371   0.01782   0.01005  -0.0788   0.9164   0.0679
  -3.500  -0.0029   0.01671   0.00898  -0.0798   0.9093   0.0705
  -3.250   0.0269   0.01606   0.00830  -0.0798   0.8985   0.0739
  -3.000   0.0565   0.01543   0.00757  -0.0796   0.8878   0.0786
  -2.750   0.0865   0.01481   0.00701  -0.0796   0.8773   0.0860
  -2.500   0.1130   0.01421   0.00643  -0.0789   0.8634   0.0969
  -2.250   0.1395   0.01381   0.00602  -0.0781   0.8489   0.1141
  -2.000   0.1662   0.01357   0.00576  -0.0775   0.8346   0.1294
  -1.750   0.1927   0.01332   0.00550  -0.0768   0.8206   0.1421
  -1.500   0.2192   0.01307   0.00522  -0.0762   0.8068   0.1539
  -1.250   0.2455   0.01285   0.00497  -0.0755   0.7925   0.1681
  -1.000   0.2709   0.01259   0.00475  -0.0748   0.7768   0.1864
  -0.750   0.2962   0.01227   0.00452  -0.0740   0.7611   0.2119
  -0.500   0.3207   0.01174   0.00430  -0.0733   0.7463   0.2812
  -0.250   0.3692   0.00985   0.00447  -0.0761   0.7316   0.9732
   0.000   0.4250   0.00988   0.00427  -0.0817   0.7145   1.0000
   0.250   0.4495   0.00994   0.00417  -0.0808   0.6986   1.0000
   0.500   0.4740   0.01002   0.00408  -0.0799   0.6824   1.0000
   0.750   0.4983   0.01011   0.00403  -0.0789   0.6658   1.0000
   1.000   0.5226   0.01024   0.00399  -0.0780   0.6489   1.0000
   1.250   0.5468   0.01038   0.00399  -0.0771   0.6317   1.0000
   1.500   0.5708   0.01053   0.00401  -0.0761   0.6142   1.0000
   1.750   0.5948   0.01069   0.00404  -0.0752   0.5964   1.0000
   2.000   0.6187   0.01086   0.00410  -0.0742   0.5784   1.0000
   2.250   0.6424   0.01104   0.00415  -0.0732   0.5603   1.0000
   2.500   0.6661   0.01122   0.00422  -0.0723   0.5422   1.0000
   2.750   0.6897   0.01141   0.00430  -0.0713   0.5241   1.0000
   3.000   0.7131   0.01163   0.00439  -0.0703   0.5060   1.0000
   3.250   0.7365   0.01188   0.00451  -0.0693   0.4883   1.0000
   3.500   0.7599   0.01215   0.00466  -0.0684   0.4709   1.0000
   3.750   0.7832   0.01246   0.00485  -0.0674   0.4542   1.0000
   4.000   0.8066   0.01281   0.00507  -0.0665   0.4384   1.0000
   4.250   0.8301   0.01316   0.00533  -0.0657   0.4229   1.0000
   4.500   0.8538   0.01351   0.00562  -0.0649   0.4082   1.0000
   4.750   0.8777   0.01387   0.00592  -0.0641   0.3949   1.0000
   5.000   0.9017   0.01427   0.00624  -0.0634   0.3836   1.0000
   5.250   0.9259   0.01464   0.00655  -0.0627   0.3734   1.0000
   5.500   0.9502   0.01497   0.00687  -0.0621   0.3633   1.0000
   5.750   0.9743   0.01536   0.00716  -0.0614   0.3547   1.0000
   6.000   0.9984   0.01561   0.00748  -0.0608   0.3456   1.0000
   6.250   1.0225   0.01599   0.00777  -0.0601   0.3381   1.0000
   6.500   1.0465   0.01624   0.00809  -0.0595   0.3301   1.0000
   6.750   1.0704   0.01662   0.00839  -0.0588   0.3233   1.0000
   7.000   1.0944   0.01690   0.00877  -0.0582   0.3166   1.0000
   7.250   1.1181   0.01722   0.00909  -0.0575   0.3102   1.0000
   7.500   1.1416   0.01758   0.00947  -0.0569   0.3038   1.0000
   7.750   1.1649   0.01788   0.00983  -0.0561   0.2974   1.0000
   8.000   1.1883   0.01830   0.01020  -0.0555   0.2919   1.0000
   8.250   1.2113   0.01862   0.01064  -0.0547   0.2861   1.0000
   8.500   1.2333   0.01894   0.01101  -0.0539   0.2793   1.0000
   8.750   1.2550   0.01933   0.01144  -0.0530   0.2725   1.0000
   9.000   1.2757   0.01963   0.01183  -0.0519   0.2646   1.0000
   9.250   1.2953   0.02002   0.01226  -0.0507   0.2558   1.0000
   9.500   1.3138   0.02038   0.01266  -0.0493   0.2461   1.0000
   9.750   1.3323   0.02072   0.01313  -0.0479   0.2359   1.0000
  10.000   1.3486   0.02113   0.01360  -0.0462   0.2237   1.0000
  10.250   1.3633   0.02154   0.01410  -0.0442   0.2059   1.0000
  10.500   1.3726   0.02214   0.01463  -0.0415   0.1597   1.0000
  10.750   1.3602   0.02432   0.01628  -0.0365   0.1083   1.0000
  11.000   1.3564   0.02628   0.01817  -0.0329   0.0881   1.0000
  11.250   1.3566   0.02804   0.01992  -0.0301   0.0772   1.0000
  11.500   1.3574   0.02984   0.02174  -0.0277   0.0712   1.0000
  11.750   1.3598   0.03162   0.02359  -0.0258   0.0668   1.0000
  12.250   1.3599   0.03593   0.02804  -0.0227   0.0615   1.0000
  12.500   1.3606   0.03823   0.03043  -0.0216   0.0595   1.0000
  12.750   1.3594   0.04082   0.03309  -0.0207   0.0579   1.0000
  13.000   1.3557   0.04377   0.03610  -0.0200   0.0566   1.0000
  13.250   1.3502   0.04699   0.03935  -0.0194   0.0553   1.0000
  13.500   1.3510   0.04967   0.04217  -0.0191   0.0542   1.0000
  13.750   1.3508   0.05249   0.04509  -0.0188   0.0530   1.0000
  14.000   1.3503   0.05539   0.04807  -0.0186   0.0519   1.0000
  14.250   1.3497   0.05829   0.05104  -0.0184   0.0508   1.0000
  14.500   1.3497   0.06113   0.05392  -0.0182   0.0499   1.0000
  14.750   1.3506   0.06377   0.05657  -0.0177   0.0490   1.0000
  15.000   1.3555   0.06574   0.05851  -0.0165   0.0479   1.0000
  15.250   1.3585   0.06839   0.06130  -0.0164   0.0472   1.0000
  15.500   1.3614   0.07103   0.06406  -0.0163   0.0463   1.0000
  15.750   1.3643   0.07369   0.06683  -0.0162   0.0454   1.0000
  16.000   1.3680   0.07625   0.06946  -0.0161   0.0445   1.0000
  16.250   1.3730   0.07862   0.07190  -0.0158   0.0437   1.0000
  16.500   1.3792   0.08077   0.07410  -0.0153   0.0429   1.0000
  16.750   1.3921   0.08191   0.07519  -0.0139   0.0419   1.0000
  17.000   1.3983   0.08425   0.07762  -0.0130   0.0411   1.0000
  17.250   1.3924   0.08837   0.08196  -0.0142   0.0407   1.0000
  17.500   1.3865   0.09260   0.08639  -0.0155   0.0403   1.0000
  17.750   1.3800   0.09698   0.09097  -0.0169   0.0398   1.0000
  18.000   1.3729   0.10156   0.09574  -0.0185   0.0394   1.0000
  18.250   1.3646   0.10645   0.10083  -0.0204   0.0391   1.0000
  18.500   1.3544   0.11178   0.10636  -0.0228   0.0389   1.0000
  18.750   1.3421   0.11760   0.11239  -0.0256   0.0387   1.0000
  19.000   1.3269   0.12412   0.11912  -0.0291   0.0385   1.0000
  19.250   1.3080   0.13164   0.12686  -0.0335   0.0385   1.0000
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