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GOE 591 AIRFOIL (goe591-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 591 AIRFOIL (goe591-il)
Reynolds number: 100,000
Max Cl/Cd: 57.27 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe591-il-100000-n5.txt
Download as CSV file: xf-goe591-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 591 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2792   0.10796   0.10332  -0.0378   1.0000   0.0561
  -9.000  -0.2880   0.10633   0.10178  -0.0365   1.0000   0.0575
  -8.750  -0.3013   0.10468   0.10024  -0.0399   0.9968   0.0598
  -8.500  -0.2919   0.10039   0.09596  -0.0478   0.9880   0.0602
  -8.000  -0.2567   0.08930   0.08481  -0.0507   0.9788   0.0457
  -7.750  -0.2502   0.08384   0.07936  -0.0569   0.9685   0.0425
  -7.500  -0.2359   0.08000   0.07551  -0.0617   0.9599   0.0442
  -7.250  -0.2203   0.07471   0.07019  -0.0689   0.9502   0.0442
  -7.000  -0.2076   0.06951   0.06495  -0.0752   0.9392   0.0440
  -6.750  -0.1910   0.06284   0.05816  -0.0834   0.9302   0.0430
  -6.500  -0.1736   0.05625   0.05139  -0.0903   0.9207   0.0425
  -6.250  -0.1557   0.05220   0.04718  -0.0935   0.9113   0.0442
  -6.000  -0.1329   0.04651   0.04117  -0.0983   0.9042   0.0457
  -5.750  -0.1176   0.04114   0.03538  -0.1002   0.8940   0.0459
  -5.500  -0.0924   0.03585   0.02947  -0.1029   0.8883   0.0473
  -5.250  -0.0749   0.03208   0.02498  -0.1027   0.8783   0.0492
  -5.000  -0.0454   0.02894   0.02119  -0.1038   0.8733   0.0500
  -4.750  -0.0233   0.02729   0.01932  -0.1033   0.8640   0.0509
  -4.500   0.0095   0.02600   0.01782  -0.1044   0.8589   0.0530
  -4.250   0.0333   0.02498   0.01657  -0.1038   0.8494   0.0554
  -4.000   0.0665   0.02345   0.01466  -0.1046   0.8441   0.0571
  -3.750   0.0910   0.02238   0.01331  -0.1038   0.8347   0.0584
  -3.500   0.1244   0.02125   0.01188  -0.1045   0.8291   0.0600
  -3.250   0.1486   0.02047   0.01104  -0.1038   0.8194   0.0618
  -3.000   0.1797   0.01986   0.01037  -0.1043   0.8128   0.0658
  -2.750   0.2052   0.01935   0.00975  -0.1036   0.8033   0.0701
  -2.500   0.2340   0.01870   0.00898  -0.1035   0.7957   0.0739
  -2.250   0.2599   0.01818   0.00847  -0.1030   0.7867   0.0792
  -2.000   0.2864   0.01771   0.00793  -0.1025   0.7780   0.0884
  -1.750   0.3137   0.01725   0.00746  -0.1022   0.7694   0.1040
  -1.500   0.3386   0.01694   0.00724  -0.1015   0.7597   0.1282
  -1.250   0.3677   0.01662   0.00699  -0.1016   0.7519   0.1656
  -1.000   0.3918   0.01639   0.00689  -0.1008   0.7412   0.2155
  -0.750   0.4187   0.01595   0.00673  -0.1007   0.7321   0.2972
  -0.500   0.4410   0.01508   0.00664  -0.0997   0.7229   0.5307
  -0.250   0.5155   0.01416   0.00647  -0.1081   0.7131   1.0000
   0.250   0.5644   0.01433   0.00626  -0.1064   0.6931   1.0000
   0.500   0.5879   0.01445   0.00623  -0.1055   0.6824   1.0000
   0.750   0.6131   0.01455   0.00616  -0.1048   0.6729   1.0000
   1.000   0.6371   0.01468   0.00615  -0.1039   0.6623   1.0000
   1.250   0.6607   0.01482   0.00619  -0.1030   0.6516   1.0000
   1.500   0.6856   0.01496   0.00619  -0.1022   0.6419   1.0000
   1.750   0.7099   0.01511   0.00623  -0.1014   0.6316   1.0000
   2.000   0.7334   0.01529   0.00632  -0.1005   0.6208   1.0000
   2.250   0.7581   0.01545   0.00639  -0.0998   0.6111   1.0000
   2.500   0.7824   0.01563   0.00648  -0.0991   0.6010   1.0000
   2.750   0.8057   0.01584   0.00663  -0.0981   0.5902   1.0000
   3.000   0.8299   0.01604   0.00675  -0.0974   0.5802   1.0000
   3.250   0.8540   0.01625   0.00687  -0.0966   0.5700   1.0000
   3.500   0.8768   0.01649   0.00708  -0.0956   0.5590   1.0000
   3.750   0.9006   0.01672   0.00727  -0.0948   0.5491   1.0000
   4.000   0.9245   0.01696   0.00745  -0.0941   0.5396   1.0000
   4.250   0.9471   0.01724   0.00772  -0.0931   0.5296   1.0000
   4.500   0.9711   0.01750   0.00795  -0.0924   0.5209   1.0000
   4.750   0.9938   0.01779   0.00826  -0.0915   0.5116   1.0000
   5.000   1.0170   0.01810   0.00856  -0.0907   0.5029   1.0000
   5.250   1.0402   0.01840   0.00886  -0.0899   0.4943   1.0000
   5.500   1.0624   0.01873   0.00924  -0.0890   0.4853   1.0000
   6.000   1.1069   0.01940   0.00997  -0.0871   0.4675   1.0000
   6.250   1.1289   0.01974   0.01033  -0.0861   0.4584   1.0000
   6.500   1.1499   0.02008   0.01070  -0.0850   0.4485   1.0000
   6.750   1.1694   0.02046   0.01114  -0.0836   0.4375   1.0000
   7.000   1.1889   0.02082   0.01155  -0.0822   0.4265   1.0000
   7.250   1.2080   0.02119   0.01192  -0.0808   0.4153   1.0000
   7.500   1.2254   0.02160   0.01241  -0.0791   0.4035   1.0000
   7.750   1.2433   0.02203   0.01294  -0.0776   0.3930   1.0000
   8.000   1.2615   0.02248   0.01344  -0.0760   0.3834   1.0000
   8.250   1.2782   0.02295   0.01401  -0.0743   0.3731   1.0000
   8.500   1.2945   0.02345   0.01462  -0.0726   0.3632   1.0000
   8.750   1.3102   0.02396   0.01519  -0.0708   0.3534   1.0000
   9.000   1.3216   0.02448   0.01578  -0.0682   0.3416   1.0000
   9.250   1.3297   0.02507   0.01644  -0.0652   0.3276   1.0000
   9.500   1.3361   0.02574   0.01714  -0.0621   0.3125   1.0000
   9.750   1.3430   0.02651   0.01795  -0.0593   0.2982   1.0000
  10.000   1.3490   0.02739   0.01886  -0.0565   0.2837   1.0000
  10.250   1.3542   0.02838   0.01988  -0.0539   0.2692   1.0000
  10.500   1.3564   0.02957   0.02105  -0.0511   0.2530   1.0000
  10.750   1.3593   0.03087   0.02237  -0.0486   0.2381   1.0000
  11.000   1.3617   0.03230   0.02384  -0.0463   0.2237   1.0000
  11.250   1.3628   0.03393   0.02552  -0.0441   0.2089   1.0000
  11.500   1.3620   0.03579   0.02741  -0.0421   0.1930   1.0000
  11.750   1.3607   0.03785   0.02949  -0.0403   0.1742   1.0000
  12.000   1.3570   0.04022   0.03186  -0.0387   0.1559   1.0000
  12.500   1.3413   0.04623   0.03777  -0.0360   0.1205   1.0000
  12.750   1.3306   0.04982   0.04131  -0.0351   0.0999   1.0000
  13.250   1.2987   0.05887   0.05010  -0.0345   0.0541   1.0000
  13.500   1.2857   0.06344   0.05469  -0.0346   0.0439   1.0000
  13.750   1.2749   0.06798   0.05929  -0.0350   0.0366   1.0000
  14.000   1.2649   0.07258   0.06399  -0.0357   0.0328   1.0000
  14.250   1.2551   0.07735   0.06888  -0.0366   0.0302   1.0000
  14.500   1.2450   0.08235   0.07399  -0.0378   0.0287   1.0000
  14.750   1.2346   0.08756   0.07932  -0.0392   0.0275   1.0000
  15.000   1.2250   0.09276   0.08469  -0.0407   0.0267   1.0000
  15.250   1.2159   0.09804   0.09015  -0.0424   0.0260   1.0000
  15.500   1.2062   0.10353   0.09579  -0.0443   0.0253   1.0000
  15.750   1.1966   0.10908   0.10148  -0.0463   0.0246   1.0000
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