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GOE 413 AIRFOIL (goe413-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 413 AIRFOIL (goe413-il)
Reynolds number: 50,000
Max Cl/Cd: 23.9 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe413-il-50000-n5.txt
Download as CSV file: xf-goe413-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 413 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2591   0.11855   0.11093  -0.0478   1.0000   0.1008
 -10.250  -0.2600   0.11628   0.10875  -0.0474   1.0000   0.1005
 -10.000  -0.2663   0.11462   0.10720  -0.0459   1.0000   0.1001
  -9.750  -0.2767   0.11335   0.10603  -0.0438   1.0000   0.0996
  -9.500  -0.2616   0.10893   0.10159  -0.0482   0.9905   0.0987
  -9.250  -0.2479   0.10425   0.09689  -0.0531   0.9810   0.0976
  -9.000  -0.2365   0.09932   0.09193  -0.0581   0.9713   0.0967
  -8.750  -0.2259   0.09416   0.08674  -0.0637   0.9623   0.0962
  -8.500  -0.2174   0.08919   0.08176  -0.0689   0.9515   0.0966
  -8.250  -0.2127   0.08402   0.07657  -0.0740   0.9397   0.0969
  -8.000  -0.2115   0.07820   0.07072  -0.0798   0.9279   0.0970
  -7.750  -0.2247   0.07028   0.06275  -0.0873   0.9135   0.0964
  -7.500  -0.2757   0.05418   0.04608  -0.1049   0.8943   0.0948
  -7.250  -0.2772   0.04908   0.04055  -0.1085   0.8803   0.0951
  -7.000  -0.2623   0.04551   0.03658  -0.1112   0.8705   0.0959
  -6.750  -0.2454   0.04296   0.03371  -0.1125   0.8597   0.0972
  -6.500  -0.2235   0.04057   0.03091  -0.1140   0.8512   0.0993
  -6.250  -0.2035   0.03873   0.02873  -0.1144   0.8408   0.1012
  -6.000  -0.1744   0.03765   0.02760  -0.1152   0.8345   0.1032
  -5.750  -0.1558   0.03678   0.02662  -0.1145   0.8231   0.1050
  -5.500  -0.1281   0.03553   0.02516  -0.1150   0.8163   0.1072
  -5.250  -0.1060   0.03459   0.02402  -0.1147   0.8067   0.1095
  -5.000  -0.0799   0.03380   0.02316  -0.1148   0.7990   0.1125
  -4.750  -0.0522   0.03314   0.02243  -0.1150   0.7926   0.1168
  -4.500  -0.0305   0.03260   0.02176  -0.1145   0.7828   0.1217
  -4.250  -0.0019   0.03201   0.02118  -0.1147   0.7768   0.1274
  -4.000   0.0211   0.03158   0.02068  -0.1143   0.7683   0.1344
  -3.750   0.0469   0.03111   0.02021  -0.1142   0.7609   0.1441
  -3.500   0.0772   0.03049   0.01958  -0.1146   0.7560   0.1616
  -3.250   0.0980   0.03046   0.01964  -0.1141   0.7465   0.1817
  -3.000   0.1260   0.03019   0.01931  -0.1142   0.7403   0.2095
  -2.750   0.1548   0.03001   0.01914  -0.1143   0.7351   0.2332
  -2.500   0.1758   0.03033   0.01951  -0.1138   0.7260   0.2563
  -2.250   0.2045   0.03032   0.01947  -0.1139   0.7206   0.2827
  -2.000   0.2303   0.03043   0.01956  -0.1136   0.7142   0.3024
  -1.750   0.2534   0.03066   0.01980  -0.1131   0.7064   0.3195
  -1.500   0.2827   0.03054   0.01963  -0.1131   0.7014   0.3387
  -1.250   0.3075   0.03070   0.01980  -0.1127   0.6947   0.3583
  -1.000   0.3311   0.03092   0.02004  -0.1122   0.6873   0.3789
  -0.750   0.3608   0.03073   0.01984  -0.1121   0.6826   0.4008
  -0.500   0.3856   0.03084   0.01998  -0.1117   0.6760   0.4202
  -0.250   0.4088   0.03105   0.02023  -0.1111   0.6685   0.4396
   0.000   0.4385   0.03083   0.02003  -0.1109   0.6637   0.4637
   0.250   0.4636   0.03095   0.02020  -0.1104   0.6574   0.4895
   0.500   0.4849   0.03133   0.02066  -0.1096   0.6494   0.5178
   0.750   0.5140   0.03111   0.02049  -0.1091   0.6445   0.5537
   1.000   0.5392   0.03113   0.02060  -0.1083   0.6387   0.5918
   1.250   0.5557   0.03166   0.02131  -0.1068   0.6300   0.6301
   1.500   0.5799   0.03137   0.02121  -0.1051   0.6251   0.6816
   1.750   0.6040   0.03085   0.02086  -0.1027   0.6214   0.7540
   2.000   0.6065   0.03187   0.02217  -0.0993   0.6105   0.8439
   2.250   0.6404   0.03166   0.02186  -0.0998   0.6051   1.0000
   2.500   0.6784   0.03144   0.02138  -0.1008   0.6015   1.0000
   2.750   0.6866   0.03317   0.02310  -0.0999   0.5897   1.0000
   3.000   0.7189   0.03323   0.02299  -0.1002   0.5847   1.0000
   3.250   0.7492   0.03343   0.02304  -0.1003   0.5794   1.0000
   3.500   0.7590   0.03501   0.02462  -0.0992   0.5686   1.0000
   3.750   0.7918   0.03498   0.02446  -0.0994   0.5639   1.0000
   4.000   0.8063   0.03624   0.02571  -0.0985   0.5551   1.0000
   4.500   0.8612   0.03685   0.02616  -0.0980   0.5431   1.0000
   4.750   0.8618   0.03909   0.02846  -0.0963   0.5317   1.0000
   5.000   0.8900   0.03928   0.02859  -0.0960   0.5260   1.0000
   5.250   0.9277   0.03882   0.02804  -0.0963   0.5225   1.0000
   5.500   0.9154   0.04198   0.03130  -0.0939   0.5092   1.0000
   5.750   0.9497   0.04169   0.03095  -0.0938   0.5051   1.0000
   6.250   0.9640   0.04506   0.03437  -0.0909   0.4877   1.0000
   6.500   1.0037   0.04432   0.03358  -0.0910   0.4848   1.0000
   6.750   0.9749   0.04916   0.03853  -0.0887   0.4702   1.0000
   7.000   1.0111   0.04845   0.03779  -0.0882   0.4672   1.0000
   7.500   1.0153   0.05342   0.04285  -0.0862   0.4495   1.0000
   8.000   1.0173   0.05907   0.04859  -0.0848   0.4319   1.0000
   8.250   1.0521   0.05817   0.04770  -0.0840   0.4298   1.0000
   8.750   1.0354   0.06638   0.05603  -0.0831   0.4101   1.0000
   9.250   1.0423   0.07212   0.06188  -0.0824   0.3951   1.0000
  10.250   1.0336   0.08663   0.07662  -0.0820   0.3619   1.0000
  10.500   1.0642   0.08524   0.07525  -0.0804   0.3576   1.0000
  11.000   1.0841   0.08819   0.07831  -0.0790   0.3420   1.0000
  11.500   1.0945   0.09247   0.08270  -0.0781   0.3250   1.0000
  12.000   1.1015   0.09742   0.08779  -0.0776   0.3080   1.0000
  12.500   1.1139   0.10123   0.09172  -0.0768   0.2908   1.0000
  13.000   1.1314   0.10403   0.09464  -0.0759   0.2733   1.0000
  13.500   1.1448   0.10783   0.09860  -0.0756   0.2559   1.0000
  13.750   1.1252   0.11454   0.10542  -0.0776   0.2425   1.0000
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