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GOE 650 AIRFOIL (goe650-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 650 AIRFOIL (goe650-il)
Reynolds number: 50,000
Max Cl/Cd: 34.82 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe650-il-50000-n5.txt
Download as CSV file: xf-goe650-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 650 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3637   0.11611   0.10812  -0.0470   1.0000   0.0902
 -10.750  -0.3687   0.11250   0.10457  -0.0473   1.0000   0.0902
 -10.500  -0.3781   0.10846   0.10060  -0.0479   1.0000   0.0905
 -10.250  -0.3725   0.10697   0.09917  -0.0463   1.0000   0.0918
 -10.000  -0.3715   0.10509   0.09734  -0.0451   1.0000   0.0934
  -9.750  -0.3766   0.10253   0.09485  -0.0443   1.0000   0.0948
  -9.500  -0.3857   0.09969   0.09209  -0.0436   1.0000   0.0962
  -9.250  -0.3992   0.09643   0.08892  -0.0430   1.0000   0.0972
  -9.000  -0.4168   0.09298   0.08557  -0.0423   1.0000   0.0982
  -8.750  -0.4394   0.08930   0.08200  -0.0415   1.0000   0.0989
  -8.500  -0.4677   0.08551   0.07834  -0.0403   1.0000   0.0993
  -8.250  -0.5044   0.08114   0.07410  -0.0393   1.0000   0.0997
  -8.000  -0.5528   0.07137   0.06440  -0.0440   1.0000   0.1006
  -7.750  -0.5998   0.05661   0.04928  -0.0556   0.9996   0.1027
  -7.500  -0.5708   0.05702   0.04975  -0.0558   0.9950   0.1063
  -7.250  -0.5642   0.04643   0.03824  -0.0673   0.9878   0.1147
  -7.000  -0.5354   0.04677   0.03871  -0.0674   0.9835   0.1194
  -6.750  -0.5150   0.04227   0.03353  -0.0718   0.9782   0.1286
  -6.500  -0.4869   0.04239   0.03376  -0.0722   0.9733   0.1351
  -6.250  -0.4607   0.04034   0.03131  -0.0746   0.9686   0.1451
  -6.000  -0.4351   0.03975   0.03059  -0.0753   0.9632   0.1544
  -5.750  -0.4058   0.03929   0.03006  -0.0765   0.9586   0.1639
  -5.500  -0.3805   0.03788   0.02823  -0.0779   0.9532   0.1750
  -5.250  -0.3534   0.03783   0.02827  -0.0781   0.9477   0.1822
  -5.000  -0.3208   0.03633   0.02630  -0.0805   0.9434   0.1916
  -4.750  -0.2972   0.03602   0.02605  -0.0800   0.9367   0.1973
  -4.500  -0.2660   0.03498   0.02463  -0.0816   0.9310   0.2059
  -4.250  -0.2343   0.03446   0.02407  -0.0827   0.9255   0.2123
  -4.000  -0.2087   0.03392   0.02338  -0.0828   0.9182   0.2197
  -3.750  -0.1747   0.03329   0.02256  -0.0844   0.9129   0.2275
  -3.500  -0.1485   0.03295   0.02216  -0.0844   0.9062   0.2345
  -3.250  -0.1196   0.03249   0.02151  -0.0850   0.8997   0.2436
  -3.000  -0.0848   0.03222   0.02123  -0.0864   0.8949   0.2527
  -2.750  -0.0614   0.03194   0.02082  -0.0860   0.8873   0.2615
  -2.500  -0.0308   0.03176   0.02060  -0.0867   0.8811   0.2724
  -2.250   0.0056   0.03154   0.02037  -0.0882   0.8767   0.2844
  -2.000   0.0242   0.03146   0.02020  -0.0869   0.8675   0.2956
  -1.750   0.0574   0.03133   0.02005  -0.0879   0.8619   0.3102
  -1.500   0.0830   0.03134   0.02010  -0.0876   0.8545   0.3236
  -1.250   0.1118   0.03131   0.02006  -0.0878   0.8471   0.3397
  -1.000   0.1498   0.03120   0.01994  -0.0894   0.8424   0.3599
  -0.750   0.1685   0.03137   0.02013  -0.0881   0.8325   0.3758
  -0.500   0.2042   0.03130   0.02005  -0.0893   0.8267   0.3982
  -0.250   0.2270   0.03145   0.02022  -0.0885   0.8177   0.4168
   0.000   0.2599   0.03142   0.02019  -0.0892   0.8108   0.4401
   0.250   0.2872   0.03149   0.02031  -0.0891   0.8027   0.4607
   0.500   0.3165   0.03148   0.02037  -0.0891   0.7943   0.4827
   0.750   0.3479   0.03139   0.02034  -0.0894   0.7865   0.5068
   1.000   0.3779   0.03123   0.02024  -0.0893   0.7765   0.5318
   1.250   0.4061   0.03104   0.02015  -0.0889   0.7656   0.5569
   1.500   0.4448   0.03044   0.01965  -0.0897   0.7574   0.5878
   1.750   0.4691   0.03030   0.01962  -0.0887   0.7449   0.6162
   2.000   0.5119   0.02949   0.01898  -0.0901   0.7385   0.6552
   2.250   0.5321   0.02938   0.01909  -0.0884   0.7253   0.6949
   2.500   0.5872   0.02805   0.01837  -0.0920   0.7183   0.8627
   2.750   0.6102   0.02812   0.01831  -0.0910   0.7050   1.0000
   3.000   0.6347   0.02828   0.01836  -0.0902   0.6917   1.0000
   3.250   0.6723   0.02796   0.01792  -0.0910   0.6816   1.0000
   3.500   0.7008   0.02789   0.01778  -0.0906   0.6686   1.0000
   3.750   0.7226   0.02802   0.01787  -0.0891   0.6535   1.0000
   4.000   0.7464   0.02807   0.01787  -0.0880   0.6386   1.0000
   4.250   0.7717   0.02804   0.01781  -0.0869   0.6234   1.0000
   4.500   0.7976   0.02798   0.01771  -0.0859   0.6077   1.0000
   4.750   0.8244   0.02789   0.01757  -0.0850   0.5912   1.0000
   5.000   0.8520   0.02778   0.01742  -0.0841   0.5739   1.0000
   5.250   0.8804   0.02769   0.01726  -0.0834   0.5557   1.0000
   5.500   0.9091   0.02765   0.01713  -0.0828   0.5366   1.0000
   5.750   0.9371   0.02772   0.01710  -0.0821   0.5167   1.0000
   6.000   0.9634   0.02792   0.01718  -0.0812   0.4965   1.0000
   6.250   0.9858   0.02831   0.01745  -0.0799   0.4762   1.0000
   6.500   1.0034   0.02888   0.01798  -0.0781   0.4560   1.0000
   6.750   1.0208   0.02949   0.01852  -0.0763   0.4366   1.0000
   7.000   1.0380   0.03012   0.01908  -0.0745   0.4183   1.0000
   7.250   1.0550   0.03078   0.01969  -0.0727   0.4011   1.0000
   7.500   1.0725   0.03148   0.02031  -0.0711   0.3852   1.0000
   7.750   1.0905   0.03220   0.02094  -0.0695   0.3703   1.0000
   8.000   1.1097   0.03292   0.02155  -0.0682   0.3565   1.0000
   8.250   1.1254   0.03382   0.02248  -0.0665   0.3429   1.0000
   8.500   1.1422   0.03473   0.02339  -0.0651   0.3304   1.0000
   8.750   1.1623   0.03559   0.02420  -0.0640   0.3192   1.0000
   9.000   1.1806   0.03652   0.02513  -0.0628   0.3080   1.0000
   9.250   1.1965   0.03759   0.02628  -0.0614   0.2977   1.0000
   9.500   1.2200   0.03844   0.02705  -0.0608   0.2884   1.0000
   9.750   1.2307   0.03974   0.02852  -0.0589   0.2792   1.0000
  10.000   1.2550   0.04060   0.02931  -0.0584   0.2709   1.0000
  10.250   1.2625   0.04207   0.03101  -0.0563   0.2629   1.0000
  10.500   1.2827   0.04311   0.03205  -0.0554   0.2557   1.0000
  10.750   1.2939   0.04457   0.03366  -0.0538   0.2490   1.0000
  11.000   1.3047   0.04601   0.03526  -0.0522   0.2424   1.0000
  11.250   1.3280   0.04698   0.03618  -0.0517   0.2364   1.0000
  11.500   1.3269   0.04907   0.03857  -0.0492   0.2308   1.0000
  11.750   1.3364   0.05073   0.04039  -0.0477   0.2256   1.0000
  12.000   1.3631   0.05160   0.04120  -0.0474   0.2205   1.0000
  12.250   1.3521   0.05438   0.04433  -0.0447   0.2161   1.0000
  12.500   1.3488   0.05683   0.04700  -0.0427   0.2114   1.0000
  12.750   1.3637   0.05796   0.04815  -0.0416   0.2060   1.0000
  13.000   1.3572   0.06070   0.05109  -0.0398   0.2016   1.0000
  13.250   1.3371   0.06470   0.05538  -0.0380   0.1977   1.0000
  13.500   1.3348   0.06714   0.05793  -0.0368   0.1925   1.0000
  13.750   1.3394   0.06886   0.05968  -0.0358   0.1870   1.0000
  14.000   1.2997   0.07574   0.06689  -0.0356   0.1843   1.0000
  14.250   1.2417   0.08628   0.07775  -0.0377   0.1829   1.0000
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