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GOE 655 AIRFOIL (goe655-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 655 AIRFOIL (goe655-il)
Reynolds number: 50,000
Max Cl/Cd: 32.26 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe655-il-50000-n5.txt
Download as CSV file: xf-goe655-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 655 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3443   0.09579   0.08909  -0.0451   1.0000   0.0781
  -9.000  -0.3520   0.09301   0.08641  -0.0441   1.0000   0.0778
  -8.750  -0.3633   0.09034   0.08385  -0.0429   1.0000   0.0774
  -8.500  -0.3806   0.08767   0.08130  -0.0415   1.0000   0.0771
  -8.250  -0.4015   0.08525   0.07901  -0.0397   1.0000   0.0768
  -8.000  -0.4231   0.08224   0.07611  -0.0388   1.0000   0.0764
  -7.750  -0.4440   0.07849   0.07242  -0.0388   1.0000   0.0762
  -7.500  -0.4563   0.07279   0.06666  -0.0420   0.9965   0.0762
  -7.250  -0.4508   0.06414   0.05764  -0.0512   0.9846   0.0768
  -7.000  -0.4411   0.05719   0.05018  -0.0572   0.9738   0.0773
  -6.750  -0.4258   0.05190   0.04433  -0.0608   0.9637   0.0777
  -6.500  -0.4055   0.04751   0.03934  -0.0634   0.9547   0.0787
  -6.250  -0.3777   0.04550   0.03725  -0.0652   0.9465   0.0810
  -6.000  -0.3528   0.04340   0.03492  -0.0663   0.9375   0.0835
  -5.750  -0.3232   0.04076   0.03181  -0.0682   0.9297   0.0858
  -5.500  -0.2986   0.03853   0.02913  -0.0687   0.9202   0.0875
  -5.250  -0.2649   0.03644   0.02644  -0.0705   0.9130   0.0906
  -5.000  -0.2394   0.03518   0.02513  -0.0706   0.9031   0.0939
  -4.750  -0.2030   0.03387   0.02365  -0.0724   0.8962   0.0981
  -4.500  -0.1768   0.03273   0.02225  -0.0722   0.8857   0.1016
  -4.250  -0.1375   0.03151   0.02086  -0.0741   0.8792   0.1074
  -4.000  -0.1119   0.03077   0.02007  -0.0738   0.8677   0.1139
  -3.750  -0.0761   0.02978   0.01897  -0.0749   0.8592   0.1222
  -3.500  -0.0413   0.02892   0.01801  -0.0758   0.8491   0.1346
  -3.250  -0.0098   0.02811   0.01723  -0.0762   0.8375   0.1513
  -3.000   0.0301   0.02707   0.01631  -0.0780   0.8287   0.1845
  -2.750   0.0599   0.02627   0.01571  -0.0781   0.8163   0.2336
  -2.500   0.0875   0.02568   0.01532  -0.0777   0.8038   0.2944
  -2.250   0.1182   0.02512   0.01492  -0.0778   0.7928   0.3588
  -2.000   0.1494   0.02454   0.01455  -0.0777   0.7825   0.4318
  -1.750   0.1729   0.02409   0.01434  -0.0763   0.7696   0.5013
  -1.500   0.1996   0.02353   0.01402  -0.0752   0.7581   0.5709
  -1.250   0.2314   0.02280   0.01360  -0.0744   0.7485   0.6617
  -1.000   0.2719   0.02227   0.01344  -0.0751   0.7356   0.8112
  -0.750   0.3688   0.02184   0.01274  -0.0873   0.7225   1.0000
  -0.500   0.3943   0.02182   0.01241  -0.0867   0.7090   1.0000
  -0.250   0.4222   0.02180   0.01208  -0.0864   0.6962   1.0000
   0.000   0.4449   0.02191   0.01196  -0.0853   0.6814   1.0000
   0.250   0.4670   0.02207   0.01191  -0.0841   0.6665   1.0000
   0.500   0.4897   0.02224   0.01188  -0.0829   0.6517   1.0000
   0.750   0.5129   0.02242   0.01186  -0.0819   0.6375   1.0000
   1.000   0.5368   0.02260   0.01185  -0.0809   0.6236   1.0000
   1.250   0.5618   0.02276   0.01181  -0.0801   0.6104   1.0000
   1.500   0.5865   0.02296   0.01183  -0.0793   0.5974   1.0000
   1.750   0.6085   0.02327   0.01200  -0.0781   0.5838   1.0000
   2.000   0.6315   0.02358   0.01218  -0.0772   0.5714   1.0000
   2.250   0.6567   0.02385   0.01229  -0.0765   0.5602   1.0000
   2.500   0.6815   0.02415   0.01245  -0.0758   0.5492   1.0000
   2.750   0.7034   0.02458   0.01279  -0.0748   0.5378   1.0000
   3.000   0.7296   0.02491   0.01297  -0.0744   0.5286   1.0000
   3.250   0.7520   0.02538   0.01339  -0.0735   0.5187   1.0000
   3.500   0.7761   0.02583   0.01375  -0.0729   0.5100   1.0000
   3.750   0.7998   0.02630   0.01415  -0.0722   0.5012   1.0000
   4.000   0.8227   0.02682   0.01463  -0.0714   0.4930   1.0000
   4.250   0.8459   0.02735   0.01511  -0.0707   0.4851   1.0000
   4.500   0.8696   0.02789   0.01561  -0.0701   0.4779   1.0000
   4.750   0.8903   0.02849   0.01621  -0.0690   0.4696   1.0000
   5.000   0.9138   0.02897   0.01664  -0.0683   0.4618   1.0000
   5.250   0.9331   0.02953   0.01720  -0.0670   0.4525   1.0000
   5.500   0.9528   0.03005   0.01769  -0.0658   0.4432   1.0000
   5.750   0.9752   0.03042   0.01800  -0.0648   0.4339   1.0000
   6.000   0.9905   0.03110   0.01874  -0.0630   0.4245   1.0000
   6.250   1.0152   0.03147   0.01903  -0.0624   0.4168   1.0000
   6.500   1.0289   0.03235   0.02001  -0.0606   0.4089   1.0000
   6.750   1.0513   0.03285   0.02050  -0.0598   0.4017   1.0000
   7.000   1.0666   0.03370   0.02144  -0.0582   0.3944   1.0000
   7.250   1.0848   0.03439   0.02217  -0.0569   0.3871   1.0000
   7.500   1.1039   0.03507   0.02287  -0.0557   0.3801   1.0000
   7.750   1.1156   0.03601   0.02394  -0.0537   0.3722   1.0000
   8.000   1.1410   0.03645   0.02433  -0.0533   0.3658   1.0000
   8.250   1.1435   0.03781   0.02589  -0.0504   0.3579   1.0000
   8.500   1.1676   0.03830   0.02636  -0.0498   0.3514   1.0000
   8.750   1.1694   0.03972   0.02796  -0.0469   0.3440   1.0000
   9.000   1.1825   0.04060   0.02890  -0.0452   0.3370   1.0000
   9.250   1.1945   0.04158   0.02994  -0.0433   0.3303   1.0000
   9.500   1.1911   0.04324   0.03175  -0.0401   0.3229   1.0000
   9.750   1.2224   0.04338   0.03183  -0.0402   0.3168   1.0000
  10.000   1.1978   0.04631   0.03502  -0.0357   0.3097   1.0000
  10.250   1.2084   0.04754   0.03633  -0.0342   0.3035   1.0000
  10.500   1.2197   0.04887   0.03773  -0.0329   0.2983   1.0000
  10.750   1.1822   0.05358   0.04268  -0.0295   0.2916   1.0000
  11.000   1.1980   0.05462   0.04377  -0.0287   0.2866   1.0000
  11.250   1.1641   0.06001   0.04932  -0.0271   0.2805   1.0000
  11.500   1.1073   0.06891   0.05838  -0.0273   0.2724   1.0000
  11.750   1.1445   0.06746   0.05696  -0.0261   0.2696   1.0000
  12.000   1.0230   0.08746   0.07706  -0.0317   0.2557   1.0000
  12.250   1.0484   0.08700   0.07668  -0.0305   0.2539   1.0000
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