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GOE 285 AIRFOIL (goe285-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 285 AIRFOIL (goe285-il)
Reynolds number: 50,000
Max Cl/Cd: 34.62 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe285-il-50000-n5.txt
Download as CSV file: xf-goe285-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 285 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  -0.3487   0.11069   0.10317  -0.0283   1.0000   0.1336
  -9.000  -0.3464   0.10758   0.10010  -0.0291   1.0000   0.1340
  -8.750  -0.3812   0.09927   0.09187  -0.0382   1.0000   0.0880
  -8.500  -0.3669   0.09628   0.08887  -0.0364   1.0000   0.0864
  -8.250  -0.3671   0.09320   0.08587  -0.0363   1.0000   0.0855
  -8.000  -0.3724   0.09023   0.08300  -0.0361   1.0000   0.0847
  -7.750  -0.3799   0.08718   0.08006  -0.0362   1.0000   0.0839
  -7.500  -0.3867   0.08386   0.07683  -0.0367   1.0000   0.0830
  -7.250  -0.3943   0.08044   0.07347  -0.0372   1.0000   0.0820
  -7.000  -0.4028   0.07683   0.06990  -0.0375   1.0000   0.0808
  -6.500  -0.4304   0.06561   0.05832  -0.0411   1.0000   0.0760
  -6.250  -0.4288   0.06268   0.05532  -0.0400   1.0000   0.0757
  -6.000  -0.4260   0.05963   0.05216  -0.0392   1.0000   0.0755
  -5.750  -0.4214   0.05648   0.04884  -0.0385   1.0000   0.0753
  -5.500  -0.4145   0.05331   0.04543  -0.0380   1.0000   0.0752
  -5.250  -0.3851   0.04840   0.03992  -0.0423   0.9932   0.0759
  -5.000  -0.3534   0.04612   0.03754  -0.0451   0.9857   0.0778
  -4.750  -0.3209   0.04367   0.03484  -0.0479   0.9777   0.0797
  -4.500  -0.2864   0.04077   0.03151  -0.0508   0.9703   0.0810
  -4.250  -0.2526   0.03813   0.02841  -0.0532   0.9619   0.0824
  -4.000  -0.2180   0.03577   0.02557  -0.0553   0.9533   0.0845
  -3.750  -0.1778   0.03363   0.02287  -0.0581   0.9453   0.0885
  -3.500  -0.1431   0.03248   0.02167  -0.0598   0.9338   0.0927
  -3.250  -0.1048   0.03100   0.01987  -0.0618   0.9233   0.0976
  -3.000  -0.0624   0.02957   0.01823  -0.0644   0.9145   0.1036
  -2.750  -0.0275   0.02866   0.01714  -0.0656   0.9029   0.1133
  -2.500   0.0129   0.02772   0.01616  -0.0677   0.8945   0.1256
  -2.250   0.0486   0.02698   0.01535  -0.0690   0.8841   0.1421
  -2.000   0.0827   0.02637   0.01473  -0.0700   0.8734   0.1634
  -1.750   0.1209   0.02562   0.01403  -0.0717   0.8646   0.1871
  -1.500   0.1514   0.02504   0.01346  -0.0719   0.8523   0.2061
  -1.250   0.1852   0.02441   0.01286  -0.0727   0.8419   0.2308
  -1.000   0.2176   0.02371   0.01234  -0.0732   0.8309   0.2654
  -0.750   0.2441   0.02287   0.01204  -0.0729   0.8181   0.3472
  -0.500   0.3158   0.02073   0.01160  -0.0790   0.8113   1.0000
  -0.250   0.3415   0.02082   0.01140  -0.0782   0.7962   1.0000
   0.000   0.3674   0.02090   0.01124  -0.0774   0.7813   1.0000
   0.250   0.3940   0.02096   0.01108  -0.0767   0.7658   1.0000
   0.500   0.4203   0.02096   0.01087  -0.0758   0.7488   1.0000
   0.750   0.4463   0.02094   0.01065  -0.0747   0.7305   1.0000
   1.000   0.4720   0.02092   0.01043  -0.0736   0.7119   1.0000
   1.250   0.4977   0.02091   0.01023  -0.0724   0.6933   1.0000
   1.500   0.5232   0.02096   0.01009  -0.0714   0.6754   1.0000
   1.750   0.5484   0.02106   0.01003  -0.0704   0.6580   1.0000
   2.000   0.5734   0.02122   0.01003  -0.0694   0.6410   1.0000
   2.250   0.5981   0.02141   0.01009  -0.0684   0.6240   1.0000
   2.500   0.6225   0.02165   0.01021  -0.0675   0.6071   1.0000
   2.750   0.6466   0.02192   0.01037  -0.0665   0.5904   1.0000
   3.000   0.6705   0.02221   0.01056  -0.0656   0.5737   1.0000
   3.250   0.6942   0.02253   0.01080  -0.0646   0.5573   1.0000
   3.500   0.7178   0.02286   0.01105  -0.0637   0.5413   1.0000
   3.750   0.7415   0.02321   0.01133  -0.0628   0.5259   1.0000
   4.000   0.7652   0.02359   0.01165  -0.0619   0.5114   1.0000
   4.250   0.7894   0.02399   0.01197  -0.0611   0.4980   1.0000
   4.500   0.8141   0.02438   0.01227  -0.0604   0.4856   1.0000
   4.750   0.8379   0.02484   0.01270  -0.0596   0.4729   1.0000
   5.000   0.8613   0.02537   0.01321  -0.0588   0.4606   1.0000
   5.250   0.8857   0.02588   0.01366  -0.0582   0.4499   1.0000
   5.500   0.9099   0.02643   0.01419  -0.0576   0.4395   1.0000
   5.750   0.9331   0.02709   0.01488  -0.0569   0.4297   1.0000
   6.000   0.9584   0.02768   0.01544  -0.0564   0.4216   1.0000
   6.250   0.9811   0.02845   0.01631  -0.0558   0.4134   1.0000
   6.500   1.0054   0.02916   0.01706  -0.0553   0.4063   1.0000
   6.750   1.0297   0.02993   0.01787  -0.0549   0.4000   1.0000
   7.000   1.0508   0.03083   0.01894  -0.0541   0.3930   1.0000
   7.250   1.0757   0.03155   0.01969  -0.0537   0.3873   1.0000
   7.500   1.0963   0.03254   0.02083  -0.0529   0.3813   1.0000
   7.750   1.1164   0.03358   0.02206  -0.0521   0.3756   1.0000
   8.000   1.1400   0.03446   0.02304  -0.0517   0.3712   1.0000
   8.250   1.1609   0.03548   0.02419  -0.0509   0.3662   1.0000
   8.500   1.1756   0.03671   0.02566  -0.0495   0.3595   1.0000
   8.750   1.1999   0.03727   0.02628  -0.0489   0.3531   1.0000
   9.000   1.2111   0.03854   0.02780  -0.0471   0.3455   1.0000
   9.250   1.2321   0.03901   0.02833  -0.0460   0.3374   1.0000
   9.500   1.2414   0.04010   0.02963  -0.0439   0.3282   1.0000
   9.750   1.2632   0.04012   0.02964  -0.0427   0.3183   1.0000
  10.000   1.2678   0.04123   0.03099  -0.0400   0.3081   1.0000
  10.250   1.2774   0.04189   0.03177  -0.0378   0.2978   1.0000
  10.500   1.2934   0.04198   0.03183  -0.0359   0.2870   1.0000
  10.750   1.2893   0.04353   0.03367  -0.0327   0.2776   1.0000
  11.000   1.2921   0.04436   0.03458  -0.0298   0.2676   1.0000
  11.250   1.2954   0.04516   0.03542  -0.0272   0.2569   1.0000
  11.500   1.2843   0.04745   0.03794  -0.0244   0.2476   1.0000
  11.750   1.2822   0.04904   0.03960  -0.0224   0.2371   1.0000
  12.000   1.2736   0.05158   0.04232  -0.0208   0.2272   1.0000
  12.250   1.2615   0.05490   0.04584  -0.0198   0.2177   1.0000
  12.500   1.2547   0.05773   0.04876  -0.0192   0.2069   1.0000
  12.750   1.2339   0.06293   0.05424  -0.0198   0.1965   1.0000
  13.000   1.2107   0.06899   0.06053  -0.0212   0.1861   1.0000
  13.250   1.1868   0.07558   0.06730  -0.0231   0.1751   1.0000
  13.500   1.1630   0.08252   0.07438  -0.0254   0.1637   1.0000
  13.750   1.1483   0.08807   0.07998  -0.0272   0.1509   1.0000
  14.000   1.1541   0.08973   0.08152  -0.0270   0.1362   1.0000
  14.250   1.1564   0.09196   0.08349  -0.0268   0.1248   1.0000
  14.500   1.1555   0.09477   0.08600  -0.0269   0.1161   1.0000
  14.750   1.1456   0.09979   0.09108  -0.0282   0.1091   1.0000
  15.000   1.1456   0.10271   0.09379  -0.0284   0.1029   1.0000
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