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GOE 483 AIRFOIL (goe483-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 483 AIRFOIL (goe483-il)
Reynolds number: 1,000,000
Max Cl/Cd: 137.39 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe483-il-1000000.txt
Download as CSV file: xf-goe483-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 483 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2256   0.08653   0.08509  -0.0272   1.0000   0.0076
  -8.250  -0.2229   0.08344   0.08202  -0.0276   1.0000   0.0076
  -8.000  -0.2211   0.08044   0.07904  -0.0278   1.0000   0.0076
  -7.750  -0.2108   0.07644   0.07505  -0.0305   0.9901   0.0076
  -7.500  -0.1952   0.07165   0.07025  -0.0350   0.9816   0.0076
  -7.250  -0.1832   0.06504   0.06363  -0.0399   0.9695   0.0081
  -7.000  -0.1638   0.06121   0.05977  -0.0441   0.9519   0.0084
  -6.750  -0.1559   0.05806   0.05655  -0.0459   0.9223   0.0085
  -6.500  -0.1498   0.05564   0.05405  -0.0467   0.8983   0.0092
  -6.250  -0.1424   0.05273   0.05107  -0.0483   0.8798   0.0098
  -6.000  -0.1330   0.04948   0.04776  -0.0506   0.8651   0.0104
  -5.750  -0.1190   0.04603   0.04425  -0.0542   0.8529   0.0114
  -5.500  -0.1017   0.04284   0.04099  -0.0578   0.8428   0.0117
  -5.250  -0.0837   0.03920   0.03730  -0.0611   0.8335   0.0118
  -4.000   0.0668   0.01366   0.00985  -0.1004   0.8218   0.0088
  -3.750   0.0938   0.01232   0.00820  -0.1003   0.8140   0.0094
  -3.500   0.1209   0.01146   0.00712  -0.1002   0.8054   0.0104
  -3.250   0.1481   0.01050   0.00589  -0.1000   0.7971   0.0111
  -3.000   0.1753   0.00979   0.00496  -0.0997   0.7889   0.0116
  -2.750   0.2026   0.00885   0.00379  -0.0995   0.7810   0.0124
  -2.500   0.2297   0.00819   0.00298  -0.0992   0.7733   0.0144
  -2.250   0.2573   0.00793   0.00265  -0.0990   0.7650   0.0164
  -2.000   0.2848   0.00774   0.00238  -0.0987   0.7567   0.0178
  -1.750   0.3119   0.00725   0.00177  -0.0984   0.7478   0.0222
  -1.500   0.3395   0.00719   0.00170  -0.0982   0.7383   0.0264
  -1.250   0.3667   0.00693   0.00137  -0.0979   0.7284   0.0332
  -1.000   0.3939   0.00686   0.00123  -0.0976   0.7173   0.0380
  -0.750   0.4211   0.00673   0.00106  -0.0974   0.7049   0.0458
  -0.250   0.4752   0.00656   0.00092  -0.0969   0.6745   0.0936
   0.000   0.5022   0.00658   0.00088  -0.0966   0.6550   0.1059
   0.250   0.5289   0.00662   0.00086  -0.0963   0.6317   0.1176
   0.500   0.5554   0.00669   0.00084  -0.0960   0.6051   0.1285
   1.000   0.6084   0.00686   0.00091  -0.0954   0.5593   0.1636
   1.250   0.6352   0.00696   0.00097  -0.0952   0.5426   0.1873
   1.500   0.6620   0.00705   0.00104  -0.0950   0.5281   0.2053
   1.750   0.6888   0.00714   0.00111  -0.0947   0.5142   0.2194
   2.000   0.7157   0.00723   0.00118  -0.0945   0.5015   0.2303
   2.250   0.7427   0.00731   0.00124  -0.0944   0.4902   0.2404
   2.500   0.7696   0.00739   0.00131  -0.0942   0.4795   0.2510
   2.750   0.7965   0.00747   0.00139  -0.0940   0.4688   0.2629
   3.000   0.8235   0.00752   0.00147  -0.0938   0.4583   0.2801
   3.250   0.8503   0.00756   0.00158  -0.0937   0.4469   0.3155
   3.500   0.8776   0.00642   0.00177  -0.0940   0.4350   1.0000
   3.750   0.9040   0.00658   0.00187  -0.0937   0.4184   1.0000
   4.000   0.9300   0.00679   0.00199  -0.0934   0.3974   1.0000
   4.250   0.9555   0.00706   0.00213  -0.0930   0.3705   1.0000
   4.500   0.9808   0.00735   0.00232  -0.0926   0.3430   1.0000
   4.750   1.0059   0.00768   0.00251  -0.0922   0.3141   1.0000
   5.000   1.0306   0.00804   0.00274  -0.0918   0.2821   1.0000
   5.250   1.0535   0.00864   0.00306  -0.0911   0.2283   1.0000
   5.500   1.0659   0.01067   0.00413  -0.0892   0.0625   1.0000
   5.750   1.0868   0.01161   0.00489  -0.0881   0.0151   1.0000
   6.000   1.1113   0.01203   0.00538  -0.0875   0.0129   1.0000
   6.250   1.1356   0.01243   0.00584  -0.0869   0.0118   1.0000
   6.500   1.1594   0.01290   0.00636  -0.0862   0.0105   1.0000
   6.750   1.1817   0.01356   0.00708  -0.0853   0.0089   1.0000
   7.000   1.1976   0.01507   0.00882  -0.0834   0.0079   1.0000
   7.250   1.2207   0.01552   0.00931  -0.0826   0.0077   1.0000
   7.500   1.2421   0.01616   0.01001  -0.0817   0.0074   1.0000
   7.750   1.2624   0.01691   0.01083  -0.0805   0.0069   1.0000
   8.000   1.2817   0.01773   0.01172  -0.0792   0.0063   1.0000
   8.250   1.2984   0.01880   0.01287  -0.0776   0.0060   1.0000
   8.500   1.3137   0.02001   0.01418  -0.0757   0.0058   1.0000
   8.750   1.3309   0.02092   0.01515  -0.0743   0.0054   1.0000
   9.000   1.3464   0.02195   0.01622  -0.0727   0.0051   1.0000
   9.250   1.3554   0.02396   0.01831  -0.0702   0.0048   1.0000
   9.500   1.3670   0.02616   0.02061  -0.0681   0.0048   1.0000
   9.750   1.3810   0.02923   0.02383  -0.0665   0.0047   1.0000
  10.000   1.3933   0.03141   0.02622  -0.0646   0.0045   1.0000
  10.250   1.4053   0.03244   0.02739  -0.0626   0.0043   1.0000
  10.500   1.4140   0.03394   0.02905  -0.0601   0.0042   1.0000
  10.750   1.4196   0.03609   0.03138  -0.0574   0.0041   1.0000
  11.000   1.4216   0.03832   0.03382  -0.0543   0.0039   1.0000
  11.250   1.4181   0.04136   0.03711  -0.0511   0.0038   1.0000
  11.500   1.4095   0.04484   0.04084  -0.0480   0.0038   1.0000
  11.750   1.3957   0.04889   0.04514  -0.0452   0.0039   1.0000
  12.000   1.3785   0.05332   0.04981  -0.0432   0.0040   1.0000
  12.250   1.3606   0.05790   0.05458  -0.0422   0.0042   1.0000
  12.500   1.3577   0.06305   0.05977  -0.0418   0.0048   1.0000
  12.750   1.3480   0.06633   0.06319  -0.0417   0.0048   1.0000
  13.000   1.3325   0.07102   0.06805  -0.0424   0.0048   1.0000
  13.250   1.3140   0.07665   0.07385  -0.0441   0.0048   1.0000
  13.500   1.2997   0.08190   0.07924  -0.0462   0.0049   1.0000
  13.750   1.2828   0.08812   0.08562  -0.0493   0.0049   1.0000
  14.000   1.2658   0.09491   0.09255  -0.0530   0.0049   1.0000
  14.250   1.2486   0.10233   0.10012  -0.0574   0.0049   1.0000
  14.500   1.2317   0.11033   0.10826  -0.0624   0.0050   1.0000
  14.750   1.2141   0.11914   0.11721  -0.0680   0.0050   1.0000
  15.000   1.1950   0.12913   0.12734  -0.0746   0.0051   1.0000
  15.250   1.1655   0.14356   0.14195  -0.0845   0.0052   1.0000
  15.500   1.1307   0.16275   0.16132  -0.0965   0.0056   1.0000
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