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GOE 417 AIRFOIL (goe417-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 417 AIRFOIL (goe417-il)
Reynolds number: 50,000
Max Cl/Cd: 44.37 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe417-il-50000-n5.txt
Download as CSV file: xf-goe417-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 417 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2793   0.10622   0.09992  -0.0228   1.0000   0.0558
  -7.250  -0.2859   0.10501   0.09882  -0.0210   1.0000   0.0569
  -7.000  -0.2919   0.10385   0.09776  -0.0197   1.0000   0.0581
  -6.750  -0.2964   0.10289   0.09690  -0.0196   1.0000   0.0593
  -6.500  -0.2990   0.10222   0.09632  -0.0207   1.0000   0.0601
  -6.250  -0.2978   0.10163   0.09579  -0.0233   1.0000   0.0607
  -6.000  -0.2915   0.10071   0.09490  -0.0269   1.0000   0.0610
  -5.750  -0.2934   0.09511   0.08939  -0.0218   1.0000   0.0621
  -5.500  -0.2929   0.09139   0.08574  -0.0184   1.0000   0.0643
  -5.250  -0.2895   0.08891   0.08330  -0.0179   1.0000   0.0670
  -5.000  -0.2830   0.08675   0.08117  -0.0191   1.0000   0.0711
  -4.750  -0.2533   0.08697   0.08126  -0.0306   1.0000   0.0753
  -4.500  -0.2486   0.08095   0.07537  -0.0271   0.9962   0.0779
  -4.250  -0.2220   0.07710   0.07148  -0.0309   0.9899   0.0843
  -4.000  -0.1709   0.07380   0.06800  -0.0436   0.9823   0.0912
  -3.750  -0.1501   0.06948   0.06368  -0.0445   0.9766   0.0971
  -3.500  -0.1102   0.06604   0.06010  -0.0522   0.9689   0.1075
  -3.250  -0.0717   0.06273   0.05666  -0.0585   0.9619   0.1214
  -3.000  -0.0328   0.05949   0.05329  -0.0645   0.9547   0.1356
  -2.750   0.0042   0.05641   0.05006  -0.0694   0.9473   0.1504
  -2.500   0.0375   0.05314   0.04671  -0.0728   0.9401   0.1676
  -1.500   0.2344   0.04072   0.03280  -0.0955   0.9102   0.0999
  -1.250   0.2793   0.03808   0.02967  -0.0988   0.8998   0.0867
  -1.000   0.3247   0.03563   0.02681  -0.1022   0.8900   0.0810
  -0.750   0.3737   0.03338   0.02396  -0.1055   0.8807   0.0775
  -0.500   0.4105   0.03190   0.02223  -0.1071   0.8684   0.0811
  -0.250   0.4487   0.03045   0.02041  -0.1085   0.8568   0.0810
   0.000   0.4870   0.02912   0.01869  -0.1098   0.8462   0.0798
   0.250   0.5288   0.02782   0.01701  -0.1114   0.8376   0.0794
   0.500   0.5629   0.02696   0.01581  -0.1118   0.8250   0.0798
   0.750   0.5964   0.02619   0.01480  -0.1120   0.8121   0.0807
   1.000   0.6291   0.02549   0.01394  -0.1121   0.7988   0.0837
   1.250   0.6607   0.02494   0.01321  -0.1120   0.7848   0.0899
   1.500   0.6917   0.02434   0.01260  -0.1120   0.7700   0.0959
   1.750   0.7221   0.02386   0.01204  -0.1117   0.7543   0.1012
   2.000   0.7526   0.02341   0.01157  -0.1114   0.7377   0.1099
   2.250   0.7837   0.02296   0.01119  -0.1113   0.7208   0.1338
   2.500   0.8124   0.02136   0.01099  -0.1110   0.7020   1.0000
   2.750   0.8408   0.02139   0.01071  -0.1103   0.6818   1.0000
   3.000   0.8708   0.02139   0.01046  -0.1098   0.6624   1.0000
   3.250   0.8983   0.02154   0.01041  -0.1091   0.6412   1.0000
   3.500   0.9259   0.02172   0.01042  -0.1085   0.6201   1.0000
   3.750   0.9529   0.02200   0.01051  -0.1078   0.5995   1.0000
   4.000   0.9779   0.02238   0.01077  -0.1070   0.5781   1.0000
   4.250   1.0035   0.02277   0.01107  -0.1062   0.5584   1.0000
   4.500   1.0278   0.02324   0.01144  -0.1054   0.5390   1.0000
   4.750   1.0512   0.02373   0.01187  -0.1044   0.5194   1.0000
   5.000   1.0746   0.02422   0.01232  -0.1035   0.5006   1.0000
   5.500   1.1196   0.02528   0.01327  -0.1014   0.4638   1.0000
   5.750   1.1416   0.02586   0.01384  -0.1003   0.4466   1.0000
   6.000   1.1637   0.02647   0.01450  -0.0993   0.4306   1.0000
   6.250   1.1858   0.02711   0.01516  -0.0983   0.4157   1.0000
   6.500   1.2079   0.02778   0.01589  -0.0974   0.4018   1.0000
   6.750   1.2300   0.02849   0.01667  -0.0965   0.3886   1.0000
   7.000   1.2522   0.02923   0.01752  -0.0956   0.3760   1.0000
   7.250   1.2746   0.03000   0.01838  -0.0947   0.3641   1.0000
   7.500   1.2951   0.03086   0.01942  -0.0937   0.3517   1.0000
   7.750   1.3156   0.03176   0.02050  -0.0927   0.3398   1.0000
   8.000   1.3366   0.03269   0.02164  -0.0917   0.3289   1.0000
   8.250   1.3590   0.03359   0.02267  -0.0909   0.3191   1.0000
   8.500   1.3775   0.03474   0.02414  -0.0897   0.3089   1.0000
   8.750   1.3987   0.03585   0.02549  -0.0888   0.3006   1.0000
   9.000   1.4165   0.03676   0.02661  -0.0874   0.2899   1.0000
   9.250   1.4265   0.03757   0.02771  -0.0849   0.2760   1.0000
   9.500   1.4334   0.03831   0.02868  -0.0821   0.2613   1.0000
   9.750   1.4347   0.03898   0.02948  -0.0786   0.2446   1.0000
  10.000   1.4299   0.03997   0.03071  -0.0746   0.2258   1.0000
  10.250   1.4235   0.04118   0.03202  -0.0707   0.2058   1.0000
  10.500   1.4163   0.04284   0.03371  -0.0674   0.1834   1.0000
  10.750   1.4082   0.04507   0.03592  -0.0647   0.1590   1.0000
  11.000   1.3998   0.04793   0.03879  -0.0626   0.1295   1.0000
  11.500   1.3705   0.05621   0.04673  -0.0602   0.0655   1.0000
  11.750   1.3539   0.06124   0.05170  -0.0601   0.0597   1.0000
  12.000   1.3379   0.06661   0.05711  -0.0607   0.0558   1.0000
  12.250   1.3242   0.07203   0.06272  -0.0616   0.0526   1.0000
  12.500   1.3100   0.07783   0.06869  -0.0631   0.0502   1.0000
  12.750   1.2961   0.08380   0.07483  -0.0649   0.0484   1.0000
  13.000   1.2820   0.09000   0.08117  -0.0669   0.0468   1.0000
  13.250   1.2686   0.09619   0.08746  -0.0690   0.0453   1.0000
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