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GOE 285 AIRFOIL (goe285-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 285 AIRFOIL (goe285-il)
Reynolds number: 100,000
Max Cl/Cd: 50.14 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe285-il-100000-n5.txt
Download as CSV file: xf-goe285-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3673   0.09097   0.08563  -0.0365   1.0000   0.0540
  -8.500  -0.3727   0.08738   0.08211  -0.0375   1.0000   0.0537
  -8.000  -0.4308   0.07490   0.06982  -0.0437   1.0000   0.0507
  -7.750  -0.4379   0.07171   0.06665  -0.0433   1.0000   0.0505
  -7.500  -0.4458   0.06856   0.06352  -0.0425   1.0000   0.0502
  -7.250  -0.4544   0.06523   0.06017  -0.0416   1.0000   0.0499
  -7.000  -0.4383   0.05871   0.05344  -0.0476   0.9935   0.0495
  -6.750  -0.4187   0.05147   0.04585  -0.0537   0.9851   0.0492
  -6.500  -0.3995   0.04427   0.03812  -0.0583   0.9763   0.0492
  -6.250  -0.3787   0.03745   0.03046  -0.0616   0.9682   0.0504
  -6.000  -0.3511   0.03394   0.02646  -0.0636   0.9614   0.0511
  -5.750  -0.3220   0.03183   0.02408  -0.0649   0.9543   0.0517
  -5.500  -0.2901   0.02984   0.02178  -0.0665   0.9478   0.0524
  -5.250  -0.2582   0.02805   0.01970  -0.0679   0.9413   0.0533
  -5.000  -0.2257   0.02639   0.01775  -0.0692   0.9339   0.0544
  -4.750  -0.1912   0.02486   0.01589  -0.0706   0.9269   0.0562
  -4.500  -0.1582   0.02358   0.01436  -0.0715   0.9171   0.0585
  -4.250  -0.1251   0.02277   0.01350  -0.0725   0.9064   0.0604
  -4.000  -0.0891   0.02174   0.01233  -0.0738   0.8975   0.0628
  -3.750  -0.0592   0.02082   0.01124  -0.0739   0.8856   0.0654
  -3.500  -0.0273   0.02005   0.01045  -0.0745   0.8765   0.0683
  -3.250   0.0036   0.01945   0.00980  -0.0748   0.8663   0.0732
  -3.000   0.0329   0.01887   0.00922  -0.0749   0.8555   0.0797
  -2.750   0.0645   0.01827   0.00856  -0.0753   0.8463   0.0890
  -2.500   0.0918   0.01786   0.00816  -0.0749   0.8338   0.0990
  -2.250   0.1205   0.01752   0.00783  -0.0749   0.8226   0.1107
  -2.000   0.1500   0.01723   0.00752  -0.0749   0.8119   0.1237
  -1.750   0.1769   0.01706   0.00736  -0.0745   0.7987   0.1409
  -1.500   0.2043   0.01683   0.00713  -0.0742   0.7861   0.1589
  -1.250   0.2315   0.01650   0.00682  -0.0737   0.7729   0.1734
  -1.000   0.2584   0.01618   0.00650  -0.0732   0.7585   0.1903
  -0.750   0.2847   0.01588   0.00624  -0.0725   0.7421   0.2144
  -0.500   0.3106   0.01549   0.00601  -0.0719   0.7240   0.2646
  -0.250   0.3331   0.01459   0.00587  -0.0708   0.7047   0.4827
   0.000   0.3852   0.01351   0.00589  -0.0738   0.6830   0.9562
   0.250   0.4320   0.01356   0.00568  -0.0774   0.6641   1.0000
   0.500   0.4563   0.01366   0.00559  -0.0765   0.6481   1.0000
   0.750   0.4806   0.01378   0.00553  -0.0755   0.6322   1.0000
   1.000   0.5048   0.01393   0.00550  -0.0746   0.6164   1.0000
   1.250   0.5290   0.01408   0.00550  -0.0737   0.6008   1.0000
   1.500   0.5531   0.01425   0.00552  -0.0728   0.5850   1.0000
   1.750   0.5772   0.01443   0.00557  -0.0719   0.5688   1.0000
   2.000   0.6012   0.01462   0.00563  -0.0710   0.5522   1.0000
   2.250   0.6251   0.01481   0.00571  -0.0701   0.5351   1.0000
   2.500   0.6489   0.01502   0.00581  -0.0692   0.5179   1.0000
   2.750   0.6726   0.01525   0.00591  -0.0682   0.5009   1.0000
   3.000   0.6963   0.01550   0.00604  -0.0673   0.4846   1.0000
   3.250   0.7199   0.01577   0.00618  -0.0664   0.4692   1.0000
   3.500   0.7436   0.01607   0.00636  -0.0656   0.4547   1.0000
   3.750   0.7673   0.01638   0.00659  -0.0647   0.4410   1.0000
   4.000   0.7912   0.01670   0.00683  -0.0639   0.4285   1.0000
   4.250   0.8149   0.01706   0.00709  -0.0632   0.4170   1.0000
   4.500   0.8386   0.01741   0.00740  -0.0624   0.4056   1.0000
   4.750   0.8626   0.01777   0.00773  -0.0617   0.3950   1.0000
   5.000   0.8862   0.01818   0.00805  -0.0609   0.3858   1.0000
   5.250   0.9103   0.01854   0.00845  -0.0603   0.3759   1.0000
   5.500   0.9340   0.01896   0.00879  -0.0595   0.3683   1.0000
   5.750   0.9581   0.01935   0.00923  -0.0589   0.3600   1.0000
   6.000   0.9819   0.01977   0.00963  -0.0583   0.3532   1.0000
   6.250   1.0060   0.02020   0.01009  -0.0576   0.3463   1.0000
   6.500   1.0297   0.02063   0.01054  -0.0570   0.3397   1.0000
   6.750   1.0534   0.02108   0.01098  -0.0564   0.3341   1.0000
   7.000   1.0767   0.02152   0.01151  -0.0557   0.3271   1.0000
   7.250   1.0993   0.02194   0.01191  -0.0549   0.3204   1.0000
   7.500   1.1213   0.02237   0.01243  -0.0540   0.3124   1.0000
   7.750   1.1428   0.02279   0.01286  -0.0530   0.3049   1.0000
   8.000   1.1640   0.02324   0.01339  -0.0521   0.2972   1.0000
   8.250   1.1846   0.02369   0.01387  -0.0510   0.2897   1.0000
   8.500   1.2052   0.02417   0.01444  -0.0500   0.2826   1.0000
   8.750   1.2252   0.02466   0.01501  -0.0489   0.2756   1.0000
   9.000   1.2445   0.02518   0.01558  -0.0477   0.2686   1.0000
   9.250   1.2624   0.02569   0.01620  -0.0464   0.2602   1.0000
   9.500   1.2796   0.02625   0.01684  -0.0449   0.2522   1.0000
   9.750   1.2955   0.02682   0.01751  -0.0433   0.2435   1.0000
  10.000   1.3106   0.02744   0.01823  -0.0417   0.2346   1.0000
  10.250   1.3227   0.02811   0.01896  -0.0396   0.2247   1.0000
  10.500   1.3336   0.02878   0.01980  -0.0374   0.2132   1.0000
  10.750   1.3432   0.02955   0.02071  -0.0351   0.2014   1.0000
  11.000   1.3520   0.03043   0.02173  -0.0329   0.1850   1.0000
  11.250   1.3580   0.03153   0.02288  -0.0306   0.1527   1.0000
  11.500   1.3500   0.03359   0.02464  -0.0276   0.1257   1.0000
  11.750   1.3428   0.03605   0.02700  -0.0252   0.1107   1.0000
  12.000   1.3364   0.03871   0.02967  -0.0233   0.0999   1.0000
  12.250   1.3287   0.04169   0.03270  -0.0219   0.0912   1.0000
  12.500   1.3235   0.04466   0.03578  -0.0210   0.0832   1.0000
  12.750   1.3150   0.04815   0.03936  -0.0204   0.0777   1.0000
  13.000   1.3067   0.05185   0.04319  -0.0203   0.0729   1.0000
  13.250   1.2946   0.05622   0.04766  -0.0207   0.0699   1.0000
  13.500   1.2843   0.06060   0.05218  -0.0214   0.0671   1.0000
  13.750   1.2723   0.06537   0.05709  -0.0224   0.0649   1.0000
  14.000   1.2589   0.07053   0.06237  -0.0237   0.0632   1.0000
  14.250   1.2446   0.07601   0.06795  -0.0252   0.0618   1.0000
  14.500   1.2310   0.08150   0.07351  -0.0269   0.0607   1.0000
  14.750   1.2227   0.08622   0.07837  -0.0282   0.0593   1.0000
  15.000   1.2158   0.09076   0.08302  -0.0294   0.0578   1.0000
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