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GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 279 (DAIMLER X) AIRFOIL (goe279-il)
Reynolds number: 500,000
Max Cl/Cd: 92.95 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe279-il-500000-n5.txt
Download as CSV file: xf-goe279-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 279 (DAIMLER X) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3230   0.10569   0.10338  -0.0285   1.0000   0.0105
  -9.000  -0.3218   0.10301   0.10073  -0.0286   1.0000   0.0105
  -8.750  -0.3227   0.10057   0.09833  -0.0282   1.0000   0.0105
  -8.500  -0.3156   0.09721   0.09499  -0.0304   0.9980   0.0105
  -8.250  -0.3011   0.09311   0.09089  -0.0348   0.9947   0.0105
  -8.000  -0.2866   0.08907   0.08686  -0.0390   0.9897   0.0105
  -7.500  -0.2565   0.08193   0.07972  -0.0459   0.9790   0.0096
  -7.250  -0.2346   0.07639   0.07417  -0.0552   0.9708   0.0105
  -7.000  -0.2151   0.07258   0.07034  -0.0597   0.9656   0.0104
  -6.750  -0.1974   0.06910   0.06684  -0.0637   0.9575   0.0100
  -6.500  -0.1752   0.06491   0.06261  -0.0695   0.9510   0.0096
  -6.250  -0.1532   0.06059   0.05824  -0.0748   0.9420   0.0093
  -6.000  -0.1284   0.05606   0.05364  -0.0804   0.9346   0.0091
  -5.750  -0.1026   0.05160   0.04909  -0.0854   0.9269   0.0091
  -5.500  -0.0747   0.04711   0.04447  -0.0902   0.9204   0.0093
  -5.250  -0.0461   0.04251   0.03971  -0.0944   0.9124   0.0096
  -5.000  -0.0122   0.03549   0.03237  -0.0995   0.9050   0.0106
  -4.750   0.0143   0.03307   0.02979  -0.1009   0.8962   0.0110
  -4.500   0.0417   0.03056   0.02711  -0.1021   0.8877   0.0114
  -4.250   0.0706   0.02747   0.02377  -0.1032   0.8797   0.0120
  -4.000   0.1039   0.02058   0.01620  -0.1047   0.8732   0.0141
  -3.750   0.1306   0.02018   0.01571  -0.1048   0.8650   0.0147
  -3.250   0.1889   0.01475   0.00942  -0.1051   0.8497   0.0185
  -3.000   0.2161   0.01479   0.00942  -0.1050   0.8400   0.0193
  -2.750   0.2439   0.01407   0.00852  -0.1049   0.8302   0.0207
  -2.500   0.2723   0.01276   0.00685  -0.1046   0.8192   0.0233
  -2.250   0.2999   0.01212   0.00607  -0.1046   0.8066   0.0245
  -2.000   0.3275   0.01180   0.00566  -0.1045   0.7940   0.0254
  -1.750   0.3551   0.01147   0.00524  -0.1043   0.7809   0.0267
  -1.500   0.3827   0.01115   0.00479  -0.1041   0.7648   0.0283
  -1.250   0.4098   0.01077   0.00425  -0.1038   0.7420   0.0293
  -1.000   0.4362   0.01052   0.00381  -0.1034   0.7052   0.0300
  -0.750   0.4618   0.01057   0.00361  -0.1027   0.6622   0.0308
  -0.500   0.4873   0.01024   0.00306  -0.1023   0.6269   0.0318
  -0.250   0.5133   0.01010   0.00277  -0.1019   0.5976   0.0327
   0.000   0.5398   0.01005   0.00260  -0.1017   0.5726   0.0335
   0.250   0.5668   0.01001   0.00247  -0.1015   0.5520   0.0343
   0.500   0.5939   0.00997   0.00236  -0.1014   0.5339   0.0351
   0.750   0.6210   0.00998   0.00229  -0.1013   0.5152   0.0362
   1.000   0.6479   0.01002   0.00225  -0.1011   0.4922   0.0376
   1.250   0.6744   0.01011   0.00221  -0.1009   0.4634   0.0385
   1.500   0.7003   0.01028   0.00221  -0.1006   0.4268   0.0395
   1.750   0.7260   0.01050   0.00226  -0.1003   0.3914   0.0406
   2.000   0.7523   0.01066   0.00229  -0.1000   0.3678   0.0426
   2.250   0.7785   0.01085   0.00237  -0.0998   0.3459   0.0461
   2.500   0.8047   0.01105   0.00247  -0.0996   0.3261   0.0508
   2.750   0.8311   0.01002   0.00280  -0.1002   0.3098   0.7229
   3.250   0.8775   0.00984   0.00301  -0.0980   0.2883   1.0000
   3.500   0.9043   0.01002   0.00314  -0.0978   0.2793   1.0000
   3.750   0.9308   0.01023   0.00330  -0.0976   0.2697   1.0000
   4.000   0.9571   0.01046   0.00346  -0.0974   0.2586   1.0000
   4.250   0.9836   0.01065   0.00362  -0.0972   0.2488   1.0000
   4.500   1.0098   0.01087   0.00381  -0.0970   0.2389   1.0000
   4.750   1.0355   0.01114   0.00401  -0.0967   0.2237   1.0000
   5.000   1.0606   0.01147   0.00423  -0.0964   0.2038   1.0000
   5.250   1.0854   0.01183   0.00450  -0.0960   0.1831   1.0000
   5.500   1.1092   0.01230   0.00483  -0.0955   0.1565   1.0000
   5.750   1.1331   0.01275   0.00517  -0.0950   0.1375   1.0000
   6.000   1.1575   0.01313   0.00551  -0.0945   0.1270   1.0000
   6.250   1.1819   0.01350   0.00585  -0.0941   0.1191   1.0000
   6.500   1.2066   0.01382   0.00618  -0.0937   0.1132   1.0000
   6.750   1.2309   0.01416   0.00653  -0.0932   0.1070   1.0000
   7.000   1.2548   0.01454   0.00691  -0.0927   0.0992   1.0000
   7.250   1.2782   0.01497   0.00730  -0.0921   0.0875   1.0000
   7.500   1.2965   0.01593   0.00800  -0.0908   0.0482   1.0000
   7.750   1.3189   0.01643   0.00851  -0.0901   0.0432   1.0000
   8.000   1.3414   0.01688   0.00902  -0.0893   0.0411   1.0000
   8.250   1.3636   0.01735   0.00954  -0.0885   0.0395   1.0000
   8.500   1.3854   0.01784   0.01008  -0.0877   0.0382   1.0000
   8.750   1.4064   0.01838   0.01068  -0.0868   0.0366   1.0000
   9.000   1.4270   0.01892   0.01131  -0.0858   0.0346   1.0000
   9.250   1.4480   0.01939   0.01185  -0.0849   0.0332   1.0000
   9.500   1.4680   0.01991   0.01246  -0.0838   0.0319   1.0000
   9.750   1.4870   0.02050   0.01312  -0.0826   0.0305   1.0000
  10.000   1.5046   0.02117   0.01384  -0.0812   0.0289   1.0000
  10.250   1.5201   0.02195   0.01471  -0.0795   0.0271   1.0000
  10.500   1.5342   0.02269   0.01553  -0.0776   0.0256   1.0000
  10.750   1.5515   0.02312   0.01605  -0.0761   0.0245   1.0000
  11.000   1.5674   0.02366   0.01667  -0.0744   0.0227   1.0000
  11.250   1.5818   0.02431   0.01737  -0.0727   0.0199   1.0000
  11.500   1.5942   0.02511   0.01821  -0.0707   0.0169   1.0000
  11.750   1.6047   0.02607   0.01914  -0.0686   0.0134   1.0000
  12.000   1.6132   0.02719   0.02032  -0.0664   0.0113   1.0000
  12.250   1.6201   0.02846   0.02166  -0.0641   0.0098   1.0000
  12.500   1.6267   0.02979   0.02310  -0.0619   0.0089   1.0000
  12.750   1.6316   0.03132   0.02473  -0.0597   0.0082   1.0000
  13.000   1.6340   0.03311   0.02662  -0.0576   0.0076   1.0000
  13.250   1.6370   0.03493   0.02857  -0.0557   0.0071   1.0000
  13.500   1.6395   0.03688   0.03065  -0.0540   0.0067   1.0000
  13.750   1.6405   0.03905   0.03295  -0.0525   0.0064   1.0000
  14.000   1.6397   0.04153   0.03556  -0.0512   0.0060   1.0000
  14.250   1.6366   0.04436   0.03853  -0.0501   0.0057   1.0000
  14.500   1.6311   0.04767   0.04198  -0.0494   0.0055   1.0000
  14.750   1.6231   0.05151   0.04596  -0.0492   0.0053   1.0000
  15.000   1.6173   0.05531   0.04992  -0.0494   0.0052   1.0000
  15.250   1.6096   0.05964   0.05440  -0.0500   0.0050   1.0000
  15.500   1.5999   0.06448   0.05941  -0.0512   0.0049   1.0000
  15.750   1.5881   0.06981   0.06490  -0.0526   0.0049   1.0000
  16.000   1.5746   0.07561   0.07085  -0.0545   0.0048   1.0000
  16.250   1.5592   0.08187   0.07727  -0.0566   0.0047   1.0000
  16.500   1.5420   0.08856   0.08412  -0.0591   0.0047   1.0000
  16.750   1.5240   0.09555   0.09126  -0.0618   0.0047   1.0000
  17.000   1.5057   0.10272   0.09858  -0.0646   0.0046   1.0000
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