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GOE 648 AIRFOIL (goe648-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 648 AIRFOIL (goe648-il)
Reynolds number: 50,000
Max Cl/Cd: 22.23 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe648-il-50000.txt
Download as CSV file: xf-goe648-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 648 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3018   0.11084   0.10426  -0.0192   1.0000   0.3166
  -8.500  -0.2698   0.10589   0.09928  -0.0176   1.0000   0.3263
  -8.250  -0.3169   0.10763   0.10124  -0.0145   1.0000   0.3343
  -8.000  -0.2794   0.10224   0.09581  -0.0131   1.0000   0.3456
  -7.750  -0.3311   0.10407   0.09787  -0.0092   1.0000   0.3531
  -7.500  -0.2936   0.09894   0.09270  -0.0079   1.0000   0.3656
  -7.250  -0.3255   0.09866   0.09260  -0.0044   1.0000   0.3739
  -7.000  -0.3102   0.09567   0.08963  -0.0024   1.0000   0.3838
  -6.750  -0.3404   0.09517   0.08929   0.0014   1.0000   0.3931
  -6.500  -0.3350   0.09301   0.08717   0.0039   1.0000   0.4051
  -6.250  -0.3433   0.09116   0.08543   0.0069   1.0000   0.4153
  -6.000  -0.5419   0.06429   0.05780  -0.0242   1.0000   0.1887
  -5.750  -0.5369   0.06069   0.05410  -0.0237   1.0000   0.1874
  -5.500  -0.5311   0.05687   0.05008  -0.0236   1.0000   0.1855
  -5.250  -0.5234   0.05295   0.04583  -0.0239   1.0000   0.1840
  -5.000  -0.5135   0.04950   0.04196  -0.0240   1.0000   0.1851
  -4.750  -0.5012   0.04642   0.03836  -0.0239   1.0000   0.1870
  -4.500  -0.4868   0.04384   0.03516  -0.0236   1.0000   0.1893
  -4.250  -0.4723   0.04248   0.03397  -0.0224   1.0000   0.1943
  -4.000  -0.4568   0.04111   0.03237  -0.0216   1.0000   0.2002
  -3.750  -0.4398   0.03955   0.03024  -0.0210   1.0000   0.2062
  -3.500  -0.4244   0.03859   0.02941  -0.0200   1.0000   0.2135
  -3.250  -0.4072   0.03768   0.02817  -0.0192   1.0000   0.2226
  -3.000  -0.3660   0.03731   0.02775  -0.0226   0.9898   0.2371
  -2.750  -0.3076   0.03717   0.02731  -0.0285   0.9701   0.2601
  -2.500  -0.2556   0.03683   0.02712  -0.0330   0.9505   0.2860
  -2.250  -0.2088   0.03634   0.02669  -0.0364   0.9318   0.3205
  -2.000  -0.1664   0.03584   0.02638  -0.0388   0.9152   0.3720
  -1.750  -0.1263   0.03528   0.02644  -0.0404   0.8995   0.4627
  -1.500  -0.0934   0.03485   0.02676  -0.0397   0.8846   0.5942
  -1.250  -0.0619   0.03453   0.02712  -0.0374   0.8703   0.7369
  -1.000   0.1614   0.03506   0.02766  -0.0665   0.8530   1.0000
  -0.750   0.1663   0.03451   0.02687  -0.0652   0.8348   1.0000
  -0.500   0.1960   0.03430   0.02636  -0.0663   0.8167   1.0000
  -0.250   0.2334   0.03412   0.02591  -0.0679   0.7985   1.0000
   0.000   0.2737   0.03387   0.02543  -0.0694   0.7804   1.0000
   0.250   0.3168   0.03349   0.02483  -0.0711   0.7625   1.0000
   0.500   0.3624   0.03298   0.02413  -0.0729   0.7448   1.0000
   0.750   0.4066   0.03244   0.02341  -0.0743   0.7271   1.0000
   1.000   0.4470   0.03195   0.02276  -0.0751   0.7093   1.0000
   1.250   0.4853   0.03153   0.02218  -0.0755   0.6917   1.0000
   1.500   0.5210   0.03124   0.02173  -0.0756   0.6743   1.0000
   1.750   0.5520   0.03119   0.02153  -0.0753   0.6573   1.0000
   2.000   0.5788   0.03138   0.02159  -0.0744   0.6409   1.0000
   2.250   0.6036   0.03173   0.02182  -0.0734   0.6254   1.0000
   2.500   0.6310   0.03205   0.02201  -0.0728   0.6115   1.0000
   2.750   0.6807   0.03151   0.02126  -0.0749   0.6003   1.0000
   3.000   0.6847   0.03289   0.02261  -0.0716   0.5860   1.0000
   3.250   0.6962   0.03407   0.02375  -0.0694   0.5737   1.0000
   3.500   0.7462   0.03356   0.02304  -0.0714   0.5640   1.0000
   3.750   0.7354   0.03582   0.02536  -0.0668   0.5519   1.0000
   4.000   0.7619   0.03645   0.02591  -0.0664   0.5424   1.0000
   4.250   0.7711   0.03788   0.02732  -0.0641   0.5321   1.0000
   4.500   0.7802   0.03945   0.02888  -0.0619   0.5231   1.0000
   4.750   0.7901   0.04098   0.03040  -0.0599   0.5139   1.0000
   5.000   0.7962   0.04285   0.03227  -0.0577   0.5056   1.0000
   5.250   0.7745   0.04631   0.03578  -0.0533   0.4967   1.0000
   5.500   0.8178   0.04615   0.03555  -0.0542   0.4896   1.0000
   5.750   0.6369   0.06277   0.05229  -0.0450   0.4802   1.0000
   6.000   0.8397   0.04956   0.03896  -0.0510   0.4742   1.0000
   6.250   0.6168   0.07130   0.06079  -0.0441   0.4687   1.0000
   6.500   0.5969   0.07650   0.06600  -0.0441   0.4650   1.0000
   6.750   0.4697   0.09360   0.08332  -0.0505   0.5528   1.0000
   7.000   0.4973   0.09502   0.08470  -0.0500   0.5319   1.0000
   7.250   0.5248   0.09641   0.08605  -0.0494   0.5123   1.0000
   7.500   0.5676   0.09469   0.08424  -0.0466   0.4705   1.0000
   7.750   0.5851   0.09841   0.08797  -0.0476   0.4734   1.0000
   8.000   0.4884   0.10991   0.09965  -0.0530   0.5667   1.0000
   8.250   0.4973   0.11302   0.10274  -0.0532   0.5615   1.0000
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