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GOE 518 AIRFOIL (goe518-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 518 AIRFOIL (goe518-il)
Reynolds number: 100,000
Max Cl/Cd: 39.15 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe518-il-100000-n5.txt
Download as CSV file: xf-goe518-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 518 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250   0.0178   0.11195   0.10692  -0.0920   0.9187   0.0727
 -10.000   0.0202   0.10870   0.10368  -0.0960   0.9137   0.0752
  -9.750   0.0069   0.10569   0.10070  -0.1004   0.9060   0.0760
  -9.500   0.0247   0.10199   0.09701  -0.1002   0.8999   0.0766
  -9.250   0.0542   0.09836   0.09336  -0.1017   0.8965   0.0786
  -9.000   0.0612   0.09575   0.09077  -0.1021   0.8881   0.0809
  -8.750   0.0531   0.09234   0.08738  -0.1069   0.8803   0.0846
  -8.500   0.0228   0.08959   0.08466  -0.1095   0.8672   0.0852
  -8.250   0.0589   0.08540   0.08046  -0.1093   0.8642   0.0865
  -8.000   0.0698   0.08261   0.07767  -0.1090   0.8565   0.0875
  -7.750   0.0732   0.07966   0.07473  -0.1097   0.8478   0.0885
  -7.500   0.0646   0.07720   0.07228  -0.1087   0.8368   0.0893
  -7.000   0.0058   0.06512   0.05985  -0.1085   0.8129   0.0599
  -6.750   0.0123   0.06266   0.05735  -0.1070   0.8039   0.0587
  -6.500   0.0123   0.05949   0.05406  -0.1056   0.7943   0.0580
  -6.250   0.0074   0.05683   0.05128  -0.1026   0.7825   0.0577
  -5.750  -0.0099   0.04785   0.04144  -0.0957   0.7612   0.0536
  -5.500   0.0116   0.04506   0.03845  -0.0956   0.7553   0.0532
  -5.250   0.0118   0.04336   0.03660  -0.0914   0.7417   0.0530
  -5.000   0.0235   0.04100   0.03397  -0.0892   0.7322   0.0527
  -4.750   0.0370   0.03870   0.03137  -0.0869   0.7222   0.0525
  -4.500   0.0480   0.03674   0.02910  -0.0841   0.7109   0.0524
  -4.250   0.0699   0.03428   0.02612  -0.0829   0.7028   0.0531
  -4.000   0.0827   0.03260   0.02399  -0.0800   0.6908   0.0536
  -3.750   0.1097   0.03086   0.02190  -0.0795   0.6817   0.0539
  -3.500   0.1332   0.02953   0.02029  -0.0784   0.6704   0.0540
  -3.250   0.1590   0.02834   0.01886  -0.0777   0.6593   0.0544
  -3.000   0.1928   0.02708   0.01730  -0.0784   0.6486   0.0548
  -2.750   0.2158   0.02629   0.01631  -0.0772   0.6355   0.0553
  -2.500   0.2441   0.02550   0.01531  -0.0770   0.6234   0.0561
  -2.250   0.2760   0.02476   0.01434  -0.0774   0.6113   0.0575
  -2.000   0.2972   0.02430   0.01371  -0.0759   0.5984   0.0591
  -1.750   0.3234   0.02380   0.01299  -0.0752   0.5863   0.0602
  -1.500   0.3490   0.02333   0.01241  -0.0746   0.5738   0.0611
  -1.250   0.3678   0.02308   0.01212  -0.0728   0.5611   0.0619
  -1.000   0.3893   0.02282   0.01178  -0.0715   0.5488   0.0632
  -0.750   0.4097   0.02261   0.01148  -0.0699   0.5369   0.0646
  -0.500   0.4274   0.02249   0.01128  -0.0679   0.5253   0.0663
  -0.250   0.4485   0.02237   0.01104  -0.0665   0.5148   0.0689
   0.000   0.4659   0.02236   0.01102  -0.0646   0.5040   0.0723
   0.250   0.4865   0.02233   0.01086  -0.0631   0.4945   0.0763
   0.500   0.5059   0.02234   0.01083  -0.0616   0.4850   0.0805
   0.750   0.5277   0.02237   0.01077  -0.0604   0.4763   0.0878
   1.000   0.5492   0.02243   0.01079  -0.0593   0.4674   0.1034
   1.250   0.5767   0.02233   0.01075  -0.0594   0.4599   0.1567
   1.750   0.7972   0.02207   0.01215  -0.0936   0.4365   1.0000
   2.000   0.8134   0.02236   0.01229  -0.0916   0.4310   1.0000
   2.250   0.8328   0.02266   0.01238  -0.0901   0.4263   1.0000
   2.500   0.8493   0.02297   0.01260  -0.0882   0.4213   1.0000
   2.750   0.8654   0.02330   0.01284  -0.0863   0.4163   1.0000
   3.000   0.8828   0.02362   0.01304  -0.0846   0.4117   1.0000
   3.250   0.9043   0.02395   0.01318  -0.0836   0.4078   1.0000
   3.500   0.9204   0.02432   0.01350  -0.0817   0.4037   1.0000
   3.750   0.9368   0.02470   0.01383  -0.0799   0.3996   1.0000
   4.000   0.9550   0.02507   0.01413  -0.0784   0.3961   1.0000
   4.250   0.9749   0.02544   0.01440  -0.0773   0.3929   1.0000
   4.500   0.9986   0.02581   0.01463  -0.0768   0.3900   1.0000
   4.750   1.0170   0.02624   0.01502  -0.0754   0.3871   1.0000
   5.000   1.0325   0.02671   0.01550  -0.0736   0.3840   1.0000
   5.250   1.0494   0.02718   0.01595  -0.0721   0.3811   1.0000
   5.500   1.0675   0.02763   0.01637  -0.0708   0.3782   1.0000
   5.750   1.0865   0.02806   0.01674  -0.0696   0.3754   1.0000
   6.000   1.1086   0.02848   0.01708  -0.0690   0.3729   1.0000
   6.250   1.1325   0.02893   0.01743  -0.0687   0.3705   1.0000
   6.500   1.1430   0.02956   0.01814  -0.0663   0.3680   1.0000
   6.750   1.1557   0.03019   0.01883  -0.0643   0.3655   1.0000
   7.000   1.1703   0.03081   0.01949  -0.0626   0.3632   1.0000
   7.250   1.1857   0.03143   0.02011  -0.0611   0.3608   1.0000
   7.500   1.2033   0.03202   0.02071  -0.0600   0.3589   1.0000
   7.750   1.2221   0.03258   0.02126  -0.0590   0.3569   1.0000
   8.000   1.2437   0.03311   0.02176  -0.0586   0.3551   1.0000
   8.250   1.2696   0.03359   0.02217  -0.0587   0.3533   1.0000
   8.500   1.2758   0.03451   0.02320  -0.0561   0.3513   1.0000
   8.750   1.2768   0.03559   0.02443  -0.0528   0.3490   1.0000
   9.000   1.2805   0.03668   0.02563  -0.0501   0.3468   1.0000
   9.250   1.2861   0.03778   0.02682  -0.0477   0.3447   1.0000
   9.500   1.2940   0.03885   0.02797  -0.0458   0.3429   1.0000
   9.750   1.3039   0.03986   0.02904  -0.0441   0.3410   1.0000
  10.000   1.3175   0.04075   0.02997  -0.0429   0.3394   1.0000
  10.250   1.3342   0.04154   0.03077  -0.0421   0.3378   1.0000
  10.500   1.3570   0.04209   0.03132  -0.0420   0.3362   1.0000
  10.750   1.3742   0.04295   0.03220  -0.0413   0.3346   1.0000
  11.000   1.3372   0.04624   0.03579  -0.0352   0.3321   1.0000
  11.250   1.2921   0.05072   0.04056  -0.0296   0.3291   1.0000
  11.500   1.2265   0.05775   0.04790  -0.0243   0.3251   1.0000
  11.750   1.1973   0.06272   0.05300  -0.0221   0.3217   1.0000
  12.000   1.2141   0.06350   0.05380  -0.0217   0.3200   1.0000
  12.250   1.2359   0.06390   0.05420  -0.0215   0.3188   1.0000
  12.500   1.2698   0.06321   0.05350  -0.0217   0.3178   1.0000
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