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GOE 679 AIRFOIL (goe679-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 679 AIRFOIL (goe679-il)
Reynolds number: 100,000
Max Cl/Cd: 42.67 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe679-il-100000.txt
Download as CSV file: xf-goe679-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 679 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4029   0.12029   0.11577  -0.0278   0.9971   0.1652
  -8.750  -0.5413   0.07982   0.07512  -0.0492   0.9918   0.1057
  -8.500  -0.5960   0.06837   0.06337  -0.0549   0.9812   0.1030
  -8.250  -0.6467   0.05712   0.05146  -0.0568   0.9697   0.1016
  -8.000  -0.6592   0.05076   0.04447  -0.0564   0.9595   0.1021
  -7.750  -0.6541   0.04606   0.03909  -0.0564   0.9514   0.1034
  -7.500  -0.6426   0.04253   0.03487  -0.0558   0.9427   0.1054
  -7.250  -0.6130   0.04176   0.03424  -0.0566   0.9343   0.1079
  -7.000  -0.5806   0.04048   0.03279  -0.0581   0.9268   0.1119
  -6.750  -0.5641   0.03863   0.03050  -0.0570   0.9174   0.1159
  -6.500  -0.5236   0.03803   0.03002  -0.0594   0.9108   0.1212
  -6.250  -0.5066   0.03659   0.02820  -0.0579   0.9008   0.1267
  -6.000  -0.4657   0.03598   0.02767  -0.0602   0.8946   0.1349
  -5.750  -0.4454   0.03541   0.02711  -0.0590   0.8842   0.1426
  -5.500  -0.4057   0.03472   0.02640  -0.0609   0.8779   0.1557
  -5.250  -0.3868   0.03423   0.02578  -0.0594   0.8671   0.1672
  -5.000  -0.3460   0.03372   0.02526  -0.0614   0.8608   0.1823
  -4.750  -0.3242   0.03366   0.02526  -0.0602   0.8498   0.1927
  -4.500  -0.2832   0.03315   0.02479  -0.0621   0.8434   0.2060
  -4.250  -0.2603   0.03279   0.02432  -0.0611   0.8328   0.2169
  -4.000  -0.2213   0.03241   0.02389  -0.0626   0.8257   0.2305
  -3.750  -0.1708   0.03160   0.02320  -0.0658   0.8222   0.2449
  -3.500  -0.1571   0.03135   0.02282  -0.0632   0.8082   0.2535
  -3.250  -0.1076   0.03032   0.02181  -0.0662   0.8045   0.2662
  -3.000  -0.0894   0.02992   0.02130  -0.0643   0.7917   0.2738
  -2.750  -0.0412   0.02873   0.02011  -0.0669   0.7873   0.2848
  -2.500   0.0147   0.02727   0.01856  -0.0709   0.7845   0.2971
  -2.250   0.0331   0.02702   0.01830  -0.0689   0.7710   0.3053
  -2.000   0.0899   0.02568   0.01691  -0.0732   0.7668   0.3192
  -1.750   0.1606   0.02432   0.01547  -0.0802   0.7638   0.3372
  -1.500   0.1754   0.02410   0.01532  -0.0773   0.7488   0.3475
  -1.250   0.2460   0.02285   0.01407  -0.0845   0.7439   0.3706
  -1.000   0.2625   0.02266   0.01391  -0.0820   0.7291   0.3846
  -0.750   0.3187   0.02177   0.01306  -0.0866   0.7210   0.4124
  -0.500   0.3395   0.02149   0.01288  -0.0849   0.7071   0.4349
  -0.250   0.3673   0.02117   0.01264  -0.0844   0.6948   0.4662
   0.000   0.4098   0.02047   0.01216  -0.0865   0.6845   0.5161
   0.250   0.4265   0.02022   0.01225  -0.0840   0.6711   0.5793
   0.500   0.5389   0.01947   0.01244  -0.0979   0.6580   0.8749
   0.750   0.6581   0.01981   0.01241  -0.1138   0.6427   0.9554
   1.000   0.7493   0.02006   0.01242  -0.1258   0.6256   0.9907
   1.250   0.7871   0.02015   0.01236  -0.1282   0.6120   1.0000
   1.500   0.8103   0.02017   0.01214  -0.1275   0.6024   1.0000
   1.750   0.8143   0.02040   0.01233  -0.1233   0.5912   1.0000
   2.000   0.8372   0.02051   0.01223  -0.1223   0.5820   1.0000
   2.250   0.8443   0.02079   0.01246  -0.1186   0.5716   1.0000
   2.500   0.8699   0.02096   0.01243  -0.1181   0.5629   1.0000
   2.750   0.8758   0.02131   0.01278  -0.1141   0.5533   1.0000
   3.000   0.9072   0.02149   0.01271  -0.1146   0.5448   1.0000
   3.250   0.9086   0.02193   0.01320  -0.1097   0.5356   1.0000
   3.500   0.9360   0.02216   0.01324  -0.1096   0.5272   1.0000
   3.750   0.9440   0.02262   0.01371  -0.1059   0.5186   1.0000
   4.000   0.9641   0.02293   0.01391  -0.1044   0.5101   1.0000
   4.250   0.9835   0.02336   0.01424  -0.1028   0.5022   1.0000
   4.500   0.9934   0.02379   0.01467  -0.0994   0.4936   1.0000
   4.750   1.0287   0.02411   0.01476  -0.1007   0.4858   1.0000
   5.000   1.0266   0.02467   0.01545  -0.0953   0.4777   1.0000
   5.250   1.0508   0.02501   0.01566  -0.0945   0.4698   1.0000
   5.500   1.0658   0.02556   0.01618  -0.0922   0.4622   1.0000
   5.750   1.0753   0.02604   0.01668  -0.0888   0.4542   1.0000
   6.000   1.1136   0.02641   0.01681  -0.0907   0.4467   1.0000
   6.250   1.1071   0.02708   0.01765  -0.0846   0.4391   1.0000
   6.500   1.1279   0.02749   0.01798  -0.0833   0.4318   1.0000
   6.750   1.1494   0.02806   0.01848  -0.0822   0.4247   1.0000
   7.000   1.1501   0.02870   0.01921  -0.0774   0.4173   1.0000
   7.250   1.1817   0.02903   0.01939  -0.0781   0.4104   1.0000
   7.500   1.1865   0.02981   0.02023  -0.0742   0.4037   1.0000
   7.750   1.1912   0.03047   0.02096  -0.0703   0.3971   1.0000
   8.000   1.2283   0.03084   0.02116  -0.0719   0.3908   1.0000
   8.250   1.2270   0.03178   0.02222  -0.0671   0.3850   1.0000
   8.500   1.2260   0.03258   0.02310  -0.0624   0.3789   1.0000
   8.750   1.2589   0.03292   0.02331  -0.0634   0.3730   1.0000
   9.000   1.2678   0.03381   0.02424  -0.0604   0.3677   1.0000
   9.250   1.2526   0.03484   0.02543  -0.0536   0.3625   1.0000
   9.500   1.2657   0.03551   0.02611  -0.0514   0.3574   1.0000
   9.750   1.3237   0.03589   0.02626  -0.0566   0.3523   1.0000
  10.000   1.2898   0.03741   0.02804  -0.0472   0.3484   1.0000
  10.250   1.2732   0.03895   0.02975  -0.0411   0.3440   1.0000
  10.500   1.2835   0.03983   0.03067  -0.0389   0.3395   1.0000
  10.750   1.3394   0.03973   0.03037  -0.0430   0.3349   1.0000
  11.000   1.3092   0.04188   0.03275  -0.0356   0.3314   1.0000
  11.250   1.2645   0.04496   0.03610  -0.0276   0.3276   1.0000
  11.500   1.2410   0.04774   0.03902  -0.0230   0.3237   1.0000
  11.750   1.2651   0.04828   0.03956  -0.0227   0.3202   1.0000
  12.000   1.3510   0.04664   0.03766  -0.0285   0.3165   1.0000
  12.250   0.6865   0.13009   0.12236  -0.0293   0.3163   1.0000
  12.500   0.5845   0.14442   0.13685  -0.0362   0.3425   1.0000
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