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GOE 448 AIRFOIL (goe448-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 448 AIRFOIL (goe448-il)
Reynolds number: 200,000
Max Cl/Cd: 162.03 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe448-il-200000.txt
Download as CSV file: xf-goe448-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 448 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000   0.2707   0.09312   0.08885  -0.1459   0.8316   0.0485
  -8.750   0.2787   0.09126   0.08696  -0.1474   0.8270   0.0502
  -8.500   0.2770   0.09131   0.08705  -0.1509   0.8199   0.0509
  -8.250   0.2869   0.08806   0.08377  -0.1518   0.8160   0.0512
  -8.000   0.3047   0.08431   0.07994  -0.1508   0.8133   0.0521
  -7.750   0.3142   0.08240   0.07807  -0.1509   0.8075   0.0531
  -7.500   0.3239   0.08042   0.07608  -0.1516   0.8028   0.0543
  -7.250   0.3340   0.07837   0.07399  -0.1529   0.7990   0.0560
  -7.000   0.3361   0.07779   0.07342  -0.1551   0.7933   0.0576
  -6.750   0.3497   0.07742   0.07304  -0.1670   0.7867   0.0582
  -6.500   0.3590   0.07319   0.06878  -0.1613   0.7840   0.0586
  -6.250   0.3744   0.07037   0.06591  -0.1602   0.7815   0.0595
  -6.000   0.3835   0.06877   0.06435  -0.1602   0.7759   0.0604
  -5.750   0.3977   0.06685   0.06241  -0.1618   0.7713   0.0618
  -5.500   0.4175   0.06461   0.06011  -0.1653   0.7678   0.0638
  -5.250   0.4656   0.06221   0.05752  -0.1836   0.7635   0.0664
  -5.000   0.4676   0.05995   0.05534  -0.1795   0.7583   0.0669
  -4.750   0.4798   0.05775   0.05313  -0.1779   0.7546   0.0675
  -4.500   0.5005   0.05556   0.05088  -0.1789   0.7516   0.0687
  -4.250   0.5292   0.05325   0.04846  -0.1825   0.7491   0.0706
  -4.000   0.5449   0.05188   0.04713  -0.1841   0.7430   0.0729
  -3.750   0.5954   0.04850   0.04352  -0.1960   0.7390   0.0764
  -3.500   0.6144   0.04652   0.04151  -0.1957   0.7361   0.0774
  -3.250   0.6432   0.04456   0.03946  -0.1978   0.7338   0.0793
  -3.000   0.6971   0.04223   0.03680  -0.2084   0.7287   0.0866
  -2.750   0.7080   0.04046   0.03512  -0.2065   0.7243   0.0878
  -2.500   0.7299   0.03913   0.03377  -0.2065   0.7212   0.0900
  -2.250   0.7820   0.03654   0.03083  -0.2141   0.7188   0.0999
  -2.000   0.8039   0.03534   0.02964  -0.2141   0.7157   0.1021
  -1.750   0.8194   0.03479   0.02912  -0.2129   0.7101   0.1067
  -1.500   0.8524   0.03331   0.02749  -0.2154   0.7066   0.1170
  -1.250   0.8897   0.03193   0.02591  -0.2185   0.7040   0.1304
  -0.750   0.9414   0.03032   0.02417  -0.2195   0.6966   0.1499
  -0.500   0.9671   0.02960   0.02337  -0.2200   0.6923   0.1647
  -0.250   1.0000   0.02863   0.02225  -0.2217   0.6892   0.1801
   0.250   1.0200   0.01286   0.00592  -0.2113   0.6738   0.1426
   0.500   1.0570   0.01132   0.00420  -0.2137   0.6713   0.1351
   0.750   1.0994   0.01006   0.00242  -0.2164   0.6691   0.1295
   1.000   1.1057   0.01053   0.00290  -0.2129   0.6622   0.1286
   1.250   1.1348   0.01013   0.00235  -0.2133   0.6581   0.1280
   1.500   1.1702   0.00951   0.00156  -0.2148   0.6551   0.1284
   1.750   1.1995   0.00922   0.00123  -0.2154   0.6516   0.1309
   2.000   1.2094   0.00959   0.00167  -0.2126   0.6457   0.1319
   2.250   1.2365   0.00941   0.00144  -0.2127   0.6420   0.1328
   2.500   1.2701   0.00908   0.00105  -0.2139   0.6392   0.1343
   2.750   1.2996   0.00896   0.00090  -0.2145   0.6359   0.1364
   3.000   1.3056   0.00946   0.00152  -0.2110   0.6298   0.1377
   3.250   1.3318   0.00939   0.00143  -0.2109   0.6258   0.1411
   3.500   1.3667   0.00910   0.00113  -0.2125   0.6229   0.1468
   3.750   1.3879   0.00927   0.00137  -0.2117   0.6188   0.1526
   4.000   1.3960   0.00974   0.00192  -0.2085   0.6130   0.1580
   4.250   1.4234   0.00967   0.00189  -0.2087   0.6093   0.1734
   4.500   1.4616   0.00926   0.00165  -0.2109   0.6064   0.2880
   4.750   1.4683   0.00919   0.00249  -0.2075   0.6011   1.0000
   5.000   1.4805   0.00956   0.00285  -0.2051   0.5956   1.0000
   5.250   1.5133   0.00951   0.00269  -0.2062   0.5920   1.0000
   5.500   1.5458   0.00954   0.00263  -0.2073   0.5882   1.0000
   5.750   1.5331   0.01032   0.00355  -0.2005   0.5810   1.0000
   6.000   1.5626   0.01029   0.00344  -0.2011   0.5766   1.0000
   6.250   1.6059   0.01014   0.00316  -0.2041   0.5729   1.0000
   6.500   1.5793   0.01116   0.00437  -0.1950   0.5651   1.0000
   6.750   1.6092   0.01110   0.00426  -0.1957   0.5604   1.0000
   7.000   1.6364   0.01123   0.00434  -0.1959   0.5559   1.0000
   7.250   1.6195   0.01224   0.00548  -0.1889   0.5481   1.0000
   7.500   1.6531   0.01209   0.00528  -0.1901   0.5436   1.0000
   7.750   1.6493   0.01300   0.00628  -0.1855   0.5369   1.0000
   8.000   1.6573   0.01351   0.00681  -0.1827   0.5300   1.0000
   8.250   1.6754   0.01367   0.00693  -0.1815   0.5232   1.0000
   8.500   1.6658   0.01485   0.00820  -0.1763   0.5146   1.0000
   8.750   1.6786   0.01525   0.00858  -0.1744   0.5069   1.0000
   9.000   1.6711   0.01663   0.01004  -0.1698   0.4982   1.0000
   9.250   1.6799   0.01742   0.01083  -0.1675   0.4906   1.0000
   9.500   1.6742   0.01902   0.01249  -0.1635   0.4818   1.0000
   9.750   1.6750   0.02045   0.01395  -0.1605   0.4735   1.0000
  10.000   1.6764   0.02196   0.01549  -0.1576   0.4655   1.0000
  10.250   1.6759   0.02375   0.01735  -0.1546   0.4576   1.0000
  10.500   1.6772   0.02542   0.01904  -0.1519   0.4491   1.0000
  10.750   1.6719   0.02788   0.02157  -0.1487   0.4409   1.0000
  11.000   1.6781   0.02929   0.02296  -0.1467   0.4322   1.0000
  11.250   1.6629   0.03288   0.02667  -0.1428   0.4230   1.0000
  11.500   1.6700   0.03435   0.02809  -0.1409   0.4138   1.0000
  11.750   1.6549   0.03827   0.03213  -0.1374   0.4048   1.0000
  12.000   1.6546   0.04066   0.03455  -0.1351   0.3960   1.0000
  12.250   1.6482   0.04380   0.03773  -0.1325   0.3863   1.0000
  12.500   1.6375   0.04756   0.04157  -0.1297   0.3769   1.0000
  12.750   1.6349   0.05028   0.04426  -0.1274   0.3664   1.0000
  13.000   1.6212   0.05445   0.04852  -0.1247   0.3562   1.0000
  13.250   1.6094   0.05842   0.05254  -0.1222   0.3454   1.0000
  13.500   1.6025   0.06173   0.05584  -0.1201   0.3347   1.0000
  13.750   1.5891   0.06586   0.06005  -0.1177   0.3243   1.0000
  14.000   1.5767   0.06988   0.06414  -0.1156   0.3136   1.0000
  14.250   1.5661   0.07356   0.06785  -0.1137   0.3029   1.0000
  14.500   1.5512   0.07766   0.07198  -0.1117   0.2905   1.0000
  14.750   1.5337   0.08207   0.07647  -0.1098   0.2773   1.0000
  15.000   1.5153   0.08637   0.08082  -0.1079   0.2623   1.0000
  15.250   1.4955   0.09063   0.08510  -0.1062   0.2454   1.0000
  15.500   1.4720   0.09500   0.08946  -0.1044   0.2235   1.0000
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