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GOE 477 AIRFOIL (goe477-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 477 AIRFOIL (goe477-il)
Reynolds number: 200,000
Max Cl/Cd: 75.05 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe477-il-200000-n5.txt
Download as CSV file: xf-goe477-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 477 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1832   0.08795   0.08427  -0.0775   0.9216   0.0173
  -9.250  -0.1757   0.08284   0.07914  -0.0823   0.9134   0.0182
  -9.000  -0.1683   0.07838   0.07466  -0.0861   0.9060   0.0182
  -8.750  -0.1643   0.07394   0.07021  -0.0895   0.8991   0.0183
  -8.500  -0.1635   0.06969   0.06595  -0.0925   0.8919   0.0183
  -8.250  -0.1683   0.06544   0.06170  -0.0950   0.8847   0.0183
  -8.000  -0.1782   0.05999   0.05625  -0.0992   0.8775   0.0185
  -7.750  -0.1863   0.05224   0.04842  -0.1060   0.8714   0.0185
  -7.500  -0.2356   0.02766   0.02254  -0.1175   0.8617   0.0185
  -7.250  -0.2207   0.02433   0.01864  -0.1173   0.8587   0.0196
  -7.000  -0.1963   0.02387   0.01811  -0.1172   0.8563   0.0209
  -6.750  -0.1750   0.02253   0.01651  -0.1167   0.8531   0.0222
  -6.500  -0.1537   0.02082   0.01441  -0.1162   0.8499   0.0238
  -6.250  -0.1309   0.01942   0.01267  -0.1156   0.8471   0.0258
  -6.000  -0.1049   0.01915   0.01235  -0.1155   0.8446   0.0283
  -5.750  -0.0789   0.01864   0.01167  -0.1152   0.8424   0.0312
  -5.500  -0.0532   0.01793   0.01070  -0.1148   0.8402   0.0347
  -5.250  -0.0281   0.01772   0.01047  -0.1145   0.8373   0.0387
  -5.000  -0.0022   0.01745   0.01006  -0.1142   0.8344   0.0439
  -4.750   0.0245   0.01716   0.00950  -0.1138   0.8319   0.0486
  -4.500   0.0505   0.01679   0.00911  -0.1137   0.8296   0.0530
  -4.250   0.0776   0.01658   0.00876  -0.1135   0.8274   0.0579
  -4.000   0.1050   0.01637   0.00833  -0.1133   0.8253   0.0618
  -3.750   0.1295   0.01595   0.00796  -0.1129   0.8222   0.0658
  -3.500   0.1553   0.01572   0.00767  -0.1126   0.8192   0.0694
  -3.250   0.1817   0.01548   0.00731  -0.1122   0.8156   0.0726
  -3.000   0.2087   0.01512   0.00686  -0.1119   0.8120   0.0745
  -2.750   0.2345   0.01472   0.00644  -0.1114   0.8079   0.0764
  -2.500   0.2593   0.01446   0.00617  -0.1108   0.8030   0.0781
  -2.250   0.2856   0.01424   0.00592  -0.1104   0.7990   0.0809
  -2.000   0.3130   0.01402   0.00564  -0.1102   0.7956   0.0842
  -1.750   0.3383   0.01386   0.00544  -0.1096   0.7910   0.0865
  -1.500   0.3635   0.01362   0.00522  -0.1090   0.7855   0.0901
  -1.250   0.3908   0.01336   0.00492  -0.1087   0.7803   0.0957
  -1.000   0.4151   0.01315   0.00472  -0.1078   0.7715   0.1038
  -0.750   0.4422   0.01282   0.00441  -0.1073   0.7641   0.1217
  -0.500   0.4657   0.01258   0.00433  -0.1064   0.7548   0.1593
  -0.250   0.4923   0.01231   0.00416  -0.1061   0.7489   0.2077
   0.000   0.5160   0.01211   0.00415  -0.1053   0.7406   0.2592
   0.250   0.5412   0.01174   0.00405  -0.1048   0.7347   0.3548
   0.500   0.5568   0.01077   0.00416  -0.1024   0.7262   0.6863
   1.000   0.6517   0.01021   0.00395  -0.1101   0.7058   1.0000
   1.250   0.6755   0.01023   0.00392  -0.1091   0.6934   1.0000
   1.500   0.6998   0.01023   0.00385  -0.1082   0.6795   1.0000
   1.750   0.7242   0.01023   0.00375  -0.1073   0.6624   1.0000
   2.000   0.7483   0.01025   0.00363  -0.1063   0.6402   1.0000
   2.250   0.7713   0.01035   0.00354  -0.1051   0.6112   1.0000
   2.500   0.7925   0.01056   0.00353  -0.1036   0.5733   1.0000
   2.750   0.8107   0.01094   0.00361  -0.1016   0.5228   1.0000
   3.000   0.8264   0.01145   0.00380  -0.0993   0.4738   1.0000
   3.250   0.8433   0.01195   0.00407  -0.0973   0.4415   1.0000
   3.500   0.8621   0.01238   0.00435  -0.0956   0.4185   1.0000
   3.750   0.8816   0.01278   0.00463  -0.0942   0.3997   1.0000
   4.000   0.9015   0.01315   0.00493  -0.0928   0.3831   1.0000
   4.250   0.9218   0.01351   0.00522  -0.0915   0.3681   1.0000
   4.500   0.9420   0.01387   0.00552  -0.0902   0.3538   1.0000
   4.750   0.9619   0.01424   0.00584  -0.0889   0.3399   1.0000
   5.000   0.9816   0.01462   0.00616  -0.0875   0.3269   1.0000
   5.250   1.0013   0.01499   0.00649  -0.0862   0.3148   1.0000
   5.500   1.0214   0.01535   0.00685  -0.0849   0.3047   1.0000
   5.750   1.0404   0.01575   0.00721  -0.0835   0.2962   1.0000
   6.000   1.0605   0.01610   0.00759  -0.0823   0.2883   1.0000
   6.500   1.0983   0.01688   0.00840  -0.0794   0.2760   1.0000
   6.750   1.1161   0.01729   0.00883  -0.0778   0.2700   1.0000
   7.000   1.1334   0.01771   0.00926  -0.0761   0.2621   1.0000
   7.500   1.1653   0.01865   0.01019  -0.0726   0.2405   1.0000
   7.750   1.1820   0.01912   0.01069  -0.0710   0.2319   1.0000
   8.000   1.1972   0.01967   0.01123  -0.0692   0.2223   1.0000
   8.250   1.2137   0.02017   0.01178  -0.0677   0.2103   1.0000
   8.500   1.2284   0.02077   0.01238  -0.0660   0.1943   1.0000
   8.750   1.2415   0.02151   0.01304  -0.0642   0.1655   1.0000
   9.000   1.2304   0.02414   0.01488  -0.0600   0.0563   1.0000
   9.250   1.2359   0.02571   0.01638  -0.0575   0.0350   1.0000
   9.500   1.2459   0.02693   0.01765  -0.0556   0.0288   1.0000
   9.750   1.2566   0.02808   0.01894  -0.0538   0.0253   1.0000
  10.000   1.2667   0.02926   0.02027  -0.0521   0.0231   1.0000
  10.250   1.2743   0.03064   0.02177  -0.0502   0.0213   1.0000
  10.500   1.2764   0.03246   0.02371  -0.0481   0.0197   1.0000
  10.750   1.2831   0.03394   0.02534  -0.0464   0.0186   1.0000
  11.000   1.2865   0.03571   0.02725  -0.0446   0.0178   1.0000
  11.250   1.2884   0.03765   0.02934  -0.0429   0.0168   1.0000
  11.500   1.2890   0.03976   0.03155  -0.0413   0.0161   1.0000
  11.750   1.2870   0.04218   0.03407  -0.0398   0.0156   1.0000
  12.000   1.2816   0.04504   0.03704  -0.0384   0.0150   1.0000
  12.250   1.2805   0.04761   0.03974  -0.0373   0.0144   1.0000
  12.500   1.2787   0.05038   0.04265  -0.0364   0.0140   1.0000
  12.750   1.2756   0.05345   0.04584  -0.0358   0.0135   1.0000
  13.000   1.2724   0.05665   0.04916  -0.0353   0.0132   1.0000
  13.250   1.2694   0.05999   0.05261  -0.0351   0.0130   1.0000
  13.500   1.2665   0.06344   0.05615  -0.0351   0.0127   1.0000
  13.750   1.2639   0.06695   0.05976  -0.0353   0.0124   1.0000
  14.000   1.2612   0.07056   0.06343  -0.0356   0.0121   1.0000
  14.250   1.2589   0.07414   0.06707  -0.0359   0.0118   1.0000
  14.500   1.2596   0.07743   0.07054  -0.0361   0.0115   1.0000
  14.750   1.2602   0.08081   0.07406  -0.0365   0.0110   1.0000
  15.000   1.2611   0.08415   0.07753  -0.0370   0.0107   1.0000
  15.250   1.2619   0.08756   0.08105  -0.0375   0.0103   1.0000
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