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GOE 490 AIRFOIL (goe490-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 490 AIRFOIL (goe490-il)
Reynolds number: 50,000
Max Cl/Cd: 38.25 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe490-il-50000-n5.txt
Download as CSV file: xf-goe490-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 490 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3644   0.09746   0.09068  -0.0310   1.0000   0.0722
  -8.000  -0.3686   0.09457   0.08788  -0.0309   1.0000   0.0718
  -7.750  -0.3750   0.09182   0.08524  -0.0306   1.0000   0.0716
  -7.500  -0.3806   0.08890   0.08242  -0.0303   1.0000   0.0704
  -7.250  -0.3850   0.08567   0.07928  -0.0307   1.0000   0.0699
  -7.000  -0.3892   0.08229   0.07599  -0.0313   1.0000   0.0685
  -6.750  -0.3934   0.07858   0.07233  -0.0322   1.0000   0.0671
  -6.500  -0.3967   0.07453   0.06830  -0.0335   1.0000   0.0657
  -6.250  -0.3983   0.06998   0.06372  -0.0351   1.0000   0.0646
  -6.000  -0.3950   0.06704   0.06077  -0.0346   1.0000   0.0658
  -5.750  -0.3902   0.06425   0.05794  -0.0342   1.0000   0.0681
  -5.500  -0.3843   0.06069   0.05426  -0.0346   1.0000   0.0698
  -5.250  -0.3765   0.05664   0.05005  -0.0353   1.0000   0.0706
  -5.000  -0.3664   0.05242   0.04559  -0.0359   1.0000   0.0708
  -4.500  -0.3390   0.04355   0.03579  -0.0372   1.0000   0.0745
  -4.250  -0.3236   0.04070   0.03261  -0.0368   1.0000   0.0772
  -4.000  -0.3071   0.03856   0.03021  -0.0360   1.0000   0.0789
  -3.750  -0.2850   0.03608   0.02732  -0.0362   0.9986   0.0805
  -3.500  -0.2498   0.03344   0.02410  -0.0385   0.9924   0.0833
  -3.250  -0.2129   0.03107   0.02092  -0.0407   0.9863   0.0893
  -3.000  -0.1788   0.03024   0.02003  -0.0426   0.9784   0.0956
  -2.750  -0.1421   0.02868   0.01798  -0.0444   0.9708   0.1007
  -2.500  -0.1023   0.02748   0.01650  -0.0468   0.9620   0.1071
  -2.250  -0.0598   0.02641   0.01509  -0.0494   0.9526   0.1182
  -2.000  -0.0210   0.02572   0.01433  -0.0515   0.9413   0.1372
  -1.750   0.0182   0.02512   0.01366  -0.0537   0.9305   0.1657
  -1.500   0.0578   0.02480   0.01335  -0.0561   0.9208   0.2035
  -1.250   0.0936   0.02462   0.01320  -0.0577   0.9102   0.2406
  -1.000   0.1285   0.02426   0.01277  -0.0590   0.8993   0.2702
  -0.750   0.1670   0.02375   0.01222  -0.0609   0.8899   0.3012
  -0.500   0.2047   0.02311   0.01168  -0.0627   0.8803   0.3394
  -0.250   0.2768   0.02060   0.01121  -0.0711   0.8763   0.9993
   0.000   0.3166   0.02059   0.01082  -0.0730   0.8651   1.0000
   0.250   0.3499   0.02062   0.01058  -0.0738   0.8519   1.0000
   0.500   0.3827   0.02063   0.01039  -0.0744   0.8384   1.0000
   0.750   0.4150   0.02064   0.01022  -0.0748   0.8246   1.0000
   1.000   0.4467   0.02065   0.01009  -0.0751   0.8105   1.0000
   1.250   0.4783   0.02064   0.00997  -0.0754   0.7958   1.0000
   1.500   0.5094   0.02064   0.00987  -0.0755   0.7806   1.0000
   1.750   0.5402   0.02065   0.00979  -0.0755   0.7649   1.0000
   2.000   0.5707   0.02065   0.00971  -0.0754   0.7486   1.0000
   2.250   0.6013   0.02065   0.00964  -0.0753   0.7319   1.0000
   2.500   0.6269   0.02076   0.00969  -0.0743   0.7124   1.0000
   2.750   0.6539   0.02085   0.00973  -0.0736   0.6926   1.0000
   3.000   0.6819   0.02091   0.00971  -0.0729   0.6733   1.0000
   3.250   0.7061   0.02110   0.00985  -0.0718   0.6525   1.0000
   3.500   0.7309   0.02130   0.01002  -0.0707   0.6324   1.0000
   3.750   0.7566   0.02150   0.01015  -0.0698   0.6134   1.0000
   4.000   0.7794   0.02180   0.01044  -0.0686   0.5936   1.0000
   4.250   0.8025   0.02211   0.01074  -0.0674   0.5744   1.0000
   4.500   0.8262   0.02242   0.01105  -0.0663   0.5557   1.0000
   4.750   0.8490   0.02276   0.01137  -0.0651   0.5370   1.0000
   5.000   0.8704   0.02316   0.01179  -0.0637   0.5173   1.0000
   5.250   0.8923   0.02355   0.01219  -0.0623   0.4981   1.0000
   5.500   0.9143   0.02396   0.01256  -0.0610   0.4790   1.0000
   5.750   0.9344   0.02446   0.01309  -0.0595   0.4589   1.0000
   6.000   0.9552   0.02497   0.01362  -0.0580   0.4400   1.0000
   6.250   0.9761   0.02553   0.01422  -0.0567   0.4218   1.0000
   6.500   0.9967   0.02613   0.01485  -0.0553   0.4046   1.0000
   6.750   1.0159   0.02680   0.01562  -0.0539   0.3871   1.0000
   7.000   1.0353   0.02749   0.01642  -0.0524   0.3706   1.0000
   7.250   1.0545   0.02820   0.01725  -0.0510   0.3552   1.0000
   7.500   1.0734   0.02894   0.01816  -0.0495   0.3405   1.0000
   7.750   1.0918   0.02969   0.01904  -0.0480   0.3263   1.0000
   8.000   1.1058   0.03035   0.01980  -0.0458   0.3091   1.0000
   8.250   1.1167   0.03095   0.02043  -0.0432   0.2906   1.0000
   8.500   1.1276   0.03162   0.02113  -0.0406   0.2736   1.0000
   8.750   1.1402   0.03244   0.02208  -0.0385   0.2597   1.0000
   9.000   1.1527   0.03331   0.02313  -0.0363   0.2469   1.0000
   9.250   1.1577   0.03418   0.02409  -0.0333   0.2297   1.0000
   9.500   1.1631   0.03516   0.02520  -0.0304   0.2152   1.0000
   9.750   1.1676   0.03624   0.02645  -0.0274   0.2010   1.0000
  10.000   1.1640   0.03761   0.02787  -0.0241   0.1765   1.0000
  10.250   1.1596   0.03936   0.02958  -0.0213   0.1471   1.0000
  10.500   1.1571   0.04142   0.03164  -0.0191   0.1185   1.0000
  10.750   1.1503   0.04414   0.03421  -0.0172   0.0736   1.0000
  11.000   1.1370   0.04775   0.03752  -0.0158   0.0596   1.0000
  11.250   1.1253   0.05158   0.04125  -0.0150   0.0531   1.0000
  11.500   1.1179   0.05521   0.04504  -0.0146   0.0489   1.0000
  11.750   1.1087   0.05927   0.04925  -0.0146   0.0460   1.0000
  12.000   1.0985   0.06369   0.05381  -0.0152   0.0441   1.0000
  12.250   1.0881   0.06833   0.05859  -0.0161   0.0428   1.0000
  12.500   1.0778   0.07318   0.06354  -0.0173   0.0415   1.0000
  12.750   1.0710   0.07766   0.06821  -0.0184   0.0405   1.0000
  13.000   1.0644   0.08220   0.07293  -0.0195   0.0395   1.0000
  13.250   1.0581   0.08677   0.07766  -0.0208   0.0384   1.0000
  13.500   1.0523   0.09134   0.08237  -0.0221   0.0373   1.0000
  13.750   1.0467   0.09593   0.08708  -0.0234   0.0361   1.0000
  14.000   1.0423   0.10037   0.09162  -0.0248   0.0352   1.0000
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