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GOE 624 AIRFOIL (goe624-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 624 AIRFOIL (goe624-il)
Reynolds number: 500,000
Max Cl/Cd: 99.52 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe624-il-500000.txt
Download as CSV file: xf-goe624-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 624 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6274   0.04102   0.03765  -0.1083   0.9487   0.0340
 -11.750  -0.6437   0.03767   0.03398  -0.1068   0.9306   0.0341
 -11.500  -0.6459   0.03491   0.03095  -0.1054   0.9182   0.0342
 -11.250  -0.6395   0.03273   0.02856  -0.1043   0.9075   0.0344
 -11.000  -0.6279   0.03095   0.02660  -0.1034   0.8986   0.0346
 -10.750  -0.6139   0.02935   0.02481  -0.1025   0.8899   0.0349
 -10.500  -0.5974   0.02793   0.02321  -0.1017   0.8820   0.0352
 -10.250  -0.5793   0.02660   0.02172  -0.1009   0.8737   0.0355
 -10.000  -0.5605   0.02533   0.02024  -0.1001   0.8665   0.0358
  -9.750  -0.5398   0.02415   0.01890  -0.0996   0.8587   0.0362
  -9.500  -0.5186   0.02310   0.01764  -0.0989   0.8518   0.0367
  -9.250  -0.4962   0.02207   0.01642  -0.0984   0.8447   0.0372
  -9.000  -0.4732   0.02108   0.01523  -0.0978   0.8370   0.0375
  -8.750  -0.4495   0.02024   0.01419  -0.0973   0.8297   0.0379
  -8.500  -0.4247   0.01951   0.01329  -0.0968   0.8211   0.0382
  -8.000  -0.3763   0.01748   0.01105  -0.0959   0.8042   0.0391
  -7.750  -0.3508   0.01687   0.01036  -0.0955   0.7963   0.0396
  -7.500  -0.3244   0.01632   0.00977  -0.0953   0.7886   0.0402
  -7.250  -0.2978   0.01585   0.00922  -0.0951   0.7810   0.0409
  -7.000  -0.2710   0.01541   0.00869  -0.0948   0.7740   0.0417
  -6.750  -0.2438   0.01497   0.00818  -0.0947   0.7662   0.0425
  -6.500  -0.2167   0.01459   0.00767  -0.0944   0.7594   0.0431
  -6.250  -0.1901   0.01398   0.00704  -0.0942   0.7519   0.0439
  -6.000  -0.1632   0.01353   0.00657  -0.0940   0.7444   0.0449
  -5.750  -0.1357   0.01321   0.00620  -0.0939   0.7372   0.0461
  -5.500  -0.1079   0.01290   0.00585  -0.0938   0.7295   0.0474
  -5.250  -0.0800   0.01266   0.00550  -0.0937   0.7230   0.0487
  -5.000  -0.0524   0.01226   0.00514  -0.0937   0.7156   0.0508
  -4.750  -0.0243   0.01205   0.00488  -0.0936   0.7086   0.0534
  -4.500   0.0038   0.01180   0.00461  -0.0936   0.7017   0.0567
  -4.250   0.0323   0.01161   0.00440  -0.0936   0.6941   0.0617
  -4.000   0.0605   0.01145   0.00422  -0.0935   0.6875   0.0698
  -3.750   0.0891   0.01127   0.00409  -0.0936   0.6806   0.0801
  -3.500   0.1179   0.01122   0.00401  -0.0937   0.6738   0.0881
  -3.250   0.1463   0.01109   0.00389  -0.0938   0.6675   0.0955
  -3.000   0.1751   0.01101   0.00377  -0.0938   0.6604   0.1015
  -2.750   0.2033   0.01092   0.00365  -0.0939   0.6536   0.1078
  -2.500   0.2322   0.01085   0.00356  -0.0940   0.6465   0.1127
  -2.250   0.2604   0.01070   0.00342  -0.0940   0.6394   0.1196
  -2.000   0.2890   0.01066   0.00334  -0.0941   0.6330   0.1258
  -1.750   0.3175   0.01051   0.00324  -0.0942   0.6258   0.1360
  -1.500   0.3457   0.01043   0.00316  -0.0942   0.6189   0.1496
  -1.250   0.3741   0.01029   0.00311  -0.0943   0.6116   0.1730
  -1.000   0.4019   0.01010   0.00306  -0.0944   0.6038   0.2186
  -0.750   0.4295   0.00990   0.00304  -0.0944   0.5963   0.2813
  -0.500   0.4570   0.00966   0.00302  -0.0945   0.5881   0.3545
  -0.250   0.4838   0.00940   0.00302  -0.0944   0.5806   0.4541
   0.000   0.5094   0.00897   0.00306  -0.0941   0.5720   0.5990
   0.250   0.5320   0.00857   0.00314  -0.0929   0.5638   0.7611
   0.500   0.5532   0.00835   0.00326  -0.0909   0.5546   0.8829
   0.750   0.5837   0.00841   0.00332  -0.0910   0.5456   0.9495
   1.000   0.6246   0.00851   0.00337  -0.0936   0.5354   0.9793
   1.250   0.6698   0.00866   0.00341  -0.0973   0.5254   0.9940
   1.500   0.7100   0.00880   0.00345  -0.1001   0.5153   1.0000
   1.750   0.7343   0.00891   0.00350  -0.0994   0.5070   1.0000
   2.000   0.7583   0.00905   0.00355  -0.0987   0.4991   1.0000
   2.250   0.7827   0.00918   0.00362  -0.0980   0.4919   1.0000
   2.500   0.8072   0.00933   0.00370  -0.0974   0.4846   1.0000
   2.750   0.8317   0.00951   0.00380  -0.0968   0.4783   1.0000
   3.000   0.8573   0.00964   0.00390  -0.0964   0.4722   1.0000
   3.250   0.8824   0.00982   0.00401  -0.0960   0.4663   1.0000
   3.500   0.9078   0.01001   0.00415  -0.0956   0.4605   1.0000
   3.750   0.9338   0.01015   0.00427  -0.0953   0.4544   1.0000
   4.000   0.9588   0.01036   0.00441  -0.0948   0.4478   1.0000
   4.250   0.9846   0.01053   0.00455  -0.0945   0.4418   1.0000
   4.500   1.0106   0.01069   0.00469  -0.0943   0.4360   1.0000
   4.750   1.0359   0.01092   0.00486  -0.0939   0.4310   1.0000
   5.000   1.0616   0.01113   0.00505  -0.0937   0.4266   1.0000
   5.250   1.0879   0.01128   0.00521  -0.0935   0.4225   1.0000
   5.500   1.1136   0.01147   0.00540  -0.0933   0.4182   1.0000
   5.750   1.1388   0.01171   0.00559  -0.0929   0.4140   1.0000
   6.000   1.1642   0.01195   0.00582  -0.0927   0.4101   1.0000
   6.250   1.1899   0.01210   0.00601  -0.0924   0.4061   1.0000
   6.500   1.2151   0.01230   0.00621  -0.0921   0.4018   1.0000
   6.750   1.2394   0.01255   0.00643  -0.0917   0.3973   1.0000
   7.000   1.2638   0.01281   0.00669  -0.0913   0.3930   1.0000
   7.250   1.2886   0.01297   0.00691  -0.0909   0.3887   1.0000
   7.500   1.3127   0.01319   0.00713  -0.0905   0.3843   1.0000
   7.750   1.3355   0.01348   0.00740  -0.0898   0.3797   1.0000
   8.000   1.3586   0.01371   0.00766  -0.0892   0.3747   1.0000
   8.250   1.3812   0.01391   0.00790  -0.0885   0.3690   1.0000
   8.500   1.4019   0.01421   0.00819  -0.0875   0.3636   1.0000
   8.750   1.4226   0.01449   0.00849  -0.0865   0.3587   1.0000
   9.000   1.4424   0.01472   0.00878  -0.0853   0.3534   1.0000
   9.250   1.4598   0.01507   0.00913  -0.0838   0.3477   1.0000
   9.500   1.4779   0.01543   0.00951  -0.0824   0.3414   1.0000
   9.750   1.4957   0.01580   0.00991  -0.0811   0.3339   1.0000
  10.000   1.5118   0.01629   0.01039  -0.0796   0.3272   1.0000
  10.250   1.5300   0.01671   0.01087  -0.0785   0.3198   1.0000
  10.500   1.5442   0.01734   0.01148  -0.0769   0.3126   1.0000
  10.750   1.5618   0.01785   0.01204  -0.0759   0.3045   1.0000
  11.000   1.5746   0.01861   0.01279  -0.0743   0.2962   1.0000
  11.250   1.5887   0.01936   0.01356  -0.0730   0.2864   1.0000
  11.500   1.6005   0.02027   0.01446  -0.0715   0.2763   1.0000
  11.750   1.6091   0.02142   0.01557  -0.0697   0.2659   1.0000
  12.000   1.6194   0.02252   0.01667  -0.0683   0.2555   1.0000
  12.250   1.6284   0.02374   0.01790  -0.0668   0.2460   1.0000
  12.750   1.6436   0.02651   0.02067  -0.0639   0.2288   1.0000
  13.000   1.6477   0.02820   0.02234  -0.0624   0.2214   1.0000
  13.250   1.6565   0.02960   0.02379  -0.0613   0.2145   1.0000
  13.500   1.6587   0.03154   0.02572  -0.0598   0.2079   1.0000
  13.750   1.6669   0.03304   0.02728  -0.0588   0.2020   1.0000
  14.000   1.6699   0.03500   0.02926  -0.0576   0.1962   1.0000
  14.250   1.6737   0.03697   0.03126  -0.0566   0.1910   1.0000
  14.500   1.6793   0.03885   0.03319  -0.0557   0.1855   1.0000
  14.750   1.6786   0.04133   0.03568  -0.0547   0.1802   1.0000
  15.000   1.6834   0.04337   0.03780  -0.0540   0.1751   1.0000
  15.250   1.6849   0.04579   0.04026  -0.0534   0.1697   1.0000
  15.500   1.6817   0.04872   0.04320  -0.0526   0.1644   1.0000
  15.750   1.6857   0.05098   0.04554  -0.0522   0.1588   1.0000
  16.000   1.6818   0.05410   0.04868  -0.0517   0.1534   1.0000
  16.250   1.6823   0.05681   0.05145  -0.0513   0.1482   1.0000
  16.500   1.6800   0.05987   0.05457  -0.0510   0.1424   1.0000
  16.750   1.6741   0.06338   0.05811  -0.0507   0.1372   1.0000
  17.000   1.6713   0.06659   0.06138  -0.0506   0.1305   1.0000
  17.250   1.6628   0.07055   0.06537  -0.0506   0.1246   1.0000
  17.500   1.6561   0.07434   0.06920  -0.0507   0.1175   1.0000
  17.750   1.6461   0.07857   0.07346  -0.0508   0.1115   1.0000
  18.000   1.6353   0.08298   0.07790  -0.0512   0.1053   1.0000
  18.250   1.6251   0.08738   0.08234  -0.0516   0.1004   1.0000
  18.500   1.6144   0.09189   0.08688  -0.0521   0.0958   1.0000
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