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GOE 804 (EA 8) AIRFOIL (goe804-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 804 (EA 8) AIRFOIL (goe804-il)
Reynolds number: 500,000
Max Cl/Cd: 157.25 at α=1.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe804-il-500000-n5.txt
Download as CSV file: xf-goe804-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 804 (EA 8) AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.0620   0.08597   0.08342  -0.1069   0.9505   0.0086
  -8.000  -0.0519   0.08284   0.08029  -0.1090   0.9476   0.0082
  -7.750  -0.0388   0.07996   0.07740  -0.1114   0.9457   0.0086
  -7.500  -0.0240   0.07677   0.07421  -0.1148   0.9441   0.0098
  -7.250  -0.0082   0.07357   0.07101  -0.1182   0.9426   0.0091
  -7.000  -0.0072   0.07064   0.06810  -0.1201   0.9349   0.0104
  -6.750   0.0106   0.06711   0.06458  -0.1247   0.9322   0.0104
  -6.250   0.0547   0.05860   0.05603  -0.1359   0.9288   0.0075
  -6.000   0.0872   0.05437   0.05177  -0.1445   0.9276   0.0073
  -5.750   0.0956   0.05173   0.04912  -0.1461   0.9216   0.0071
  -5.250   0.2637   0.01492   0.01053  -0.2069   0.9175   0.0072
  -5.000   0.3022   0.01306   0.00820  -0.2102   0.9168   0.0081
  -4.750   0.3370   0.01212   0.00705  -0.2123   0.9160   0.0087
  -4.500   0.3722   0.01127   0.00598  -0.2143   0.9150   0.0096
  -4.250   0.4077   0.01054   0.00505  -0.2163   0.9139   0.0107
  -4.000   0.4427   0.01007   0.00450  -0.2181   0.9127   0.0127
  -3.750   0.4682   0.00970   0.00402  -0.2178   0.9090   0.0145
  -3.500   0.4977   0.00936   0.00362  -0.2183   0.9058   0.0178
  -3.250   0.5295   0.00902   0.00324  -0.2193   0.9034   0.0248
  -3.000   0.5609   0.00885   0.00308  -0.2202   0.9012   0.0367
  -2.750   0.5930   0.00876   0.00296  -0.2212   0.8992   0.0452
  -2.500   0.6215   0.00875   0.00287  -0.2213   0.8957   0.0497
  -2.250   0.6485   0.00856   0.00268  -0.2213   0.8906   0.0554
  -2.000   0.6784   0.00844   0.00252  -0.2218   0.8869   0.0598
  -1.750   0.7104   0.00831   0.00233  -0.2228   0.8844   0.0627
  -1.500   0.7391   0.00821   0.00223  -0.2231   0.8813   0.0665
  -1.250   0.7654   0.00815   0.00219  -0.2228   0.8771   0.0695
  -1.000   0.7939   0.00809   0.00211  -0.2230   0.8731   0.0732
  -0.750   0.8250   0.00800   0.00204  -0.2238   0.8697   0.0815
  -0.500   0.8510   0.00797   0.00204  -0.2235   0.8645   0.0922
  -0.250   0.8783   0.00794   0.00201  -0.2234   0.8585   0.1034
   0.000   0.9077   0.00786   0.00196  -0.2238   0.8529   0.1162
   0.250   0.9335   0.00782   0.00197  -0.2234   0.8452   0.1313
   0.500   0.9614   0.00772   0.00199  -0.2235   0.8355   0.1853
   0.750   0.9883   0.00766   0.00198  -0.2233   0.8220   0.2224
   1.000   1.0199   0.00731   0.00212  -0.2246   0.8091   0.4716
   1.250   1.0485   0.00684   0.00239  -0.2250   0.7965   0.8100
   1.500   1.0707   0.00686   0.00246  -0.2235   0.7802   0.8709
   1.750   1.0929   0.00695   0.00250  -0.2222   0.7560   0.8966
   2.000   1.1117   0.00716   0.00256  -0.2200   0.7212   0.9199
   2.250   1.1249   0.00742   0.00266  -0.2166   0.6792   1.0000
   2.500   1.1440   0.00788   0.00291  -0.2148   0.6396   1.0000
   2.750   1.1646   0.00828   0.00317  -0.2133   0.6088   1.0000
   3.000   1.1816   0.00885   0.00352  -0.2111   0.5592   1.0000
   3.250   1.1936   0.00970   0.00399  -0.2080   0.4802   1.0000
   3.500   1.2092   0.01046   0.00446  -0.2057   0.4265   1.0000
   3.750   1.2285   0.01102   0.00487  -0.2042   0.3907   1.0000
   4.000   1.2466   0.01165   0.00531  -0.2024   0.3428   1.0000
   4.500   1.2726   0.01376   0.00660  -0.1972   0.1924   1.0000
   4.750   1.2857   0.01491   0.00731  -0.1947   0.1104   1.0000
   5.000   1.3025   0.01574   0.00794  -0.1928   0.0685   1.0000
   5.250   1.3209   0.01643   0.00853  -0.1912   0.0483   1.0000
   5.500   1.3375   0.01730   0.00924  -0.1893   0.0183   1.0000
   5.750   1.3560   0.01800   0.00996  -0.1876   0.0125   1.0000
   6.000   1.3748   0.01866   0.01066  -0.1860   0.0098   1.0000
   6.250   1.3930   0.01937   0.01143  -0.1843   0.0084   1.0000
   6.500   1.4113   0.02007   0.01221  -0.1827   0.0074   1.0000
   6.750   1.4282   0.02093   0.01313  -0.1808   0.0065   1.0000
   7.000   1.4460   0.02167   0.01395  -0.1792   0.0058   1.0000
   7.250   1.4626   0.02252   0.01487  -0.1773   0.0052   1.0000
   7.500   1.4772   0.02358   0.01600  -0.1751   0.0049   1.0000
   7.750   1.4909   0.02473   0.01726  -0.1728   0.0046   1.0000
   8.000   1.5042   0.02593   0.01860  -0.1705   0.0043   1.0000
   8.250   1.5172   0.02717   0.01995  -0.1681   0.0041   1.0000
   8.500   1.5307   0.02840   0.02128  -0.1660   0.0038   1.0000
   8.750   1.5446   0.02949   0.02245  -0.1640   0.0035   1.0000
   9.000   1.5550   0.03114   0.02421  -0.1615   0.0033   1.0000
   9.250   1.5672   0.03269   0.02595  -0.1592   0.0031   1.0000
   9.500   1.5782   0.03454   0.02798  -0.1568   0.0030   1.0000
   9.750   1.5891   0.03651   0.03018  -0.1545   0.0029   1.0000
  10.000   1.5997   0.03857   0.03245  -0.1522   0.0027   1.0000
  10.250   1.6094   0.04065   0.03475  -0.1499   0.0026   1.0000
  10.500   1.6174   0.04303   0.03736  -0.1474   0.0025   1.0000
  10.750   1.6235   0.04528   0.03982  -0.1449   0.0024   1.0000
  11.000   1.6274   0.04785   0.04260  -0.1423   0.0024   1.0000
  11.250   1.6281   0.05071   0.04569  -0.1396   0.0023   1.0000
  11.500   1.6246   0.05432   0.04957  -0.1366   0.0023   1.0000
  11.750   1.6155   0.05870   0.05427  -0.1334   0.0022   1.0000
  12.000   1.6044   0.06330   0.05920  -0.1305   0.0022   1.0000
  12.250   1.5872   0.06899   0.06529  -0.1277   0.0022   1.0000
  12.500   1.5702   0.07447   0.07106  -0.1257   0.0022   1.0000
  12.750   1.5540   0.07996   0.07681  -0.1246   0.0022   1.0000
  13.000   1.5262   0.08803   0.08524  -0.1243   0.0022   1.0000
  13.250   1.5157   0.09307   0.09040  -0.1251   0.0022   1.0000
  13.500   1.4842   0.10330   0.10103  -0.1277   0.0021   1.0000
  13.750   1.4678   0.11064   0.10852  -0.1309   0.0022   1.0000
  14.000   1.4573   0.11714   0.11509  -0.1343   0.0022   1.0000
  14.250   1.4296   0.12956   0.12779  -0.1418   0.0022   1.0000
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