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GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 329 (PFALZ 58) AIRFOIL (goe329-il)
Reynolds number: 50,000
Max Cl/Cd: 23.6 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe329-il-50000.txt
Download as CSV file: xf-goe329-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 329 (PFALZ 58) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2789   0.11430   0.10772  -0.0337   1.0000   0.1353
  -8.500  -0.2975   0.11495   0.10855  -0.0329   1.0000   0.1368
  -8.250  -0.3205   0.11574   0.10952  -0.0307   1.0000   0.1372
  -8.000  -0.2873   0.10768   0.10140  -0.0293   1.0000   0.1443
  -7.750  -0.2981   0.10664   0.10048  -0.0268   1.0000   0.1477
  -7.500  -0.3167   0.10639   0.10037  -0.0238   1.0000   0.1501
  -7.250  -0.3372   0.10647   0.10059  -0.0221   1.0000   0.1519
  -7.000  -0.3570   0.10690   0.10114  -0.0230   1.0000   0.1531
  -6.750  -0.3509   0.10224   0.09654  -0.0192   1.0000   0.1563
  -6.500  -0.3509   0.09972   0.09406  -0.0167   1.0000   0.1612
  -6.250  -0.3590   0.09840   0.09281  -0.0167   1.0000   0.1662
  -6.000  -0.3694   0.09862   0.09309  -0.0230   1.0000   0.1695
  -5.750  -0.3647   0.09375   0.08829  -0.0160   1.0000   0.1738
  -5.500  -0.3647   0.09169   0.08627  -0.0158   1.0000   0.1809
  -5.250  -0.3639   0.08962   0.08423  -0.0193   1.0000   0.1867
  -5.000  -0.3614   0.08676   0.08143  -0.0160   1.0000   0.1936
  -4.750  -0.3561   0.08446   0.07914  -0.0192   1.0000   0.2031
  -4.500  -0.3467   0.08266   0.07729  -0.0227   1.0000   0.2170
  -4.250  -0.3458   0.07948   0.07423  -0.0180   1.0000   0.2255
  -4.000  -0.3382   0.07701   0.07176  -0.0187   1.0000   0.2393
  -3.750  -0.3241   0.07529   0.06997  -0.0228   1.0000   0.2628
  -3.500  -0.3156   0.07264   0.06737  -0.0229   1.0000   0.2807
  -3.000  -0.2755   0.06669   0.06151  -0.0240   0.9884   0.3490
  -2.750  -0.2515   0.06373   0.05863  -0.0228   0.9761   0.4161
  -2.500  -0.2364   0.06139   0.05639  -0.0187   0.9634   0.5051
  -2.250  -0.2292   0.05858   0.05373  -0.0104   0.9514   0.5726
  -2.000  -0.2197   0.05615   0.05140  -0.0020   0.9397   0.6455
  -1.750  -0.2059   0.05374   0.04905   0.0047   0.9272   0.7114
  -1.500  -0.1848   0.05133   0.04667   0.0078   0.9132   0.7600
  -1.250  -0.1465   0.04883   0.04413   0.0021   0.8974   0.7793
  -1.000   0.2407   0.04455   0.03621  -0.1049   0.8695   0.2451
  -0.750   0.2958   0.04302   0.03412  -0.1092   0.8551   0.2087
  -0.500   0.3488   0.04191   0.03237  -0.1126   0.8408   0.1831
  -0.250   0.4018   0.04061   0.03058  -0.1158   0.8281   0.1682
   0.000   0.4549   0.03899   0.02870  -0.1191   0.8166   0.1608
   0.250   0.4922   0.03829   0.02768  -0.1196   0.8018   0.1562
   0.500   0.5272   0.03767   0.02687  -0.1198   0.7873   0.1575
   0.750   0.5598   0.03720   0.02627  -0.1197   0.7731   0.1618
   1.000   0.5913   0.03682   0.02577  -0.1194   0.7595   0.1653
   1.250   0.6238   0.03640   0.02525  -0.1192   0.7469   0.1699
   1.500   0.6658   0.03531   0.02411  -0.1200   0.7378   0.1827
   1.750   0.6908   0.03538   0.02427  -0.1194   0.7239   0.2047
   2.000   0.7071   0.03394   0.02472  -0.1172   0.7111   1.0000
   2.250   0.7330   0.03458   0.02486  -0.1161   0.6991   1.0000
   2.500   0.7728   0.03415   0.02398  -0.1162   0.6914   1.0000
   2.750   0.7902   0.03535   0.02499  -0.1151   0.6782   1.0000
   3.000   0.8079   0.03661   0.02612  -0.1142   0.6662   1.0000
   3.250   0.8492   0.03598   0.02527  -0.1146   0.6601   1.0000
   3.500   0.8587   0.03800   0.02726  -0.1134   0.6475   1.0000
   3.750   0.8707   0.03991   0.02913  -0.1123   0.6365   1.0000
   4.000   0.9077   0.03964   0.02875  -0.1125   0.6302   1.0000
   4.250   0.9061   0.04292   0.03208  -0.1111   0.6188   1.0000
   4.500   0.9481   0.04226   0.03132  -0.1115   0.6139   1.0000
   4.750   0.9322   0.04695   0.03611  -0.1096   0.6020   1.0000
   5.000   0.9274   0.05082   0.04001  -0.1084   0.5933   1.0000
   5.250   0.9292   0.05409   0.04329  -0.1075   0.5860   1.0000
   5.500   0.9082   0.05965   0.04889  -0.1063   0.5787   1.0000
   5.750   0.8944   0.06449   0.05375  -0.1055   0.5725   1.0000
   6.000   0.9255   0.06534   0.05464  -0.1056   0.5682   1.0000
   6.250   0.8990   0.07162   0.06094  -0.1050   0.5650   1.0000
   6.500   0.8797   0.07704   0.06638  -0.1047   0.5632   1.0000
   6.750   0.8718   0.08159   0.07099  -0.1047   0.5632   1.0000
   7.000   0.8734   0.08569   0.07513  -0.1052   0.5652   1.0000
   7.250   0.8814   0.08947   0.07897  -0.1060   0.5676   1.0000
   7.500   0.7410   0.10508   0.09480  -0.1099   0.6948   1.0000
   7.750   0.7683   0.10889   0.09862  -0.1118   0.6905   1.0000
   8.000   0.7630   0.11020   0.09996  -0.1097   0.6795   1.0000
   8.250   0.7792   0.11337   0.10316  -0.1103   0.6735   1.0000
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