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GOE 604 AIRFOIL (goe604-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 604 AIRFOIL (goe604-il)
Reynolds number: 50,000
Max Cl/Cd: 20.58 at α=1.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe604-il-50000-n5.txt
Download as CSV file: xf-goe604-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 604 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2351   0.11439   0.10780  -0.0475   1.0000   0.0836
 -11.000  -0.2441   0.11144   0.10497  -0.0473   1.0000   0.0838
 -10.750  -0.2574   0.10867   0.10234  -0.0467   1.0000   0.0843
 -10.500  -0.2610   0.10438   0.09813  -0.0493   0.9938   0.0846
 -10.250  -0.2528   0.09802   0.09177  -0.0559   0.9804   0.0847
 -10.000  -0.2501   0.09103   0.08478  -0.0629   0.9660   0.0850
  -9.750  -0.2589   0.08221   0.07595  -0.0717   0.9505   0.0856
  -9.500  -0.2937   0.06929   0.06291  -0.0850   0.9305   0.0855
  -9.250  -0.3296   0.06060   0.05391  -0.0916   0.9073   0.0856
  -9.000  -0.3524   0.05411   0.04692  -0.0941   0.8874   0.0862
  -8.750  -0.3347   0.05203   0.04477  -0.0946   0.8712   0.0878
  -8.500  -0.3251   0.04929   0.04179  -0.0947   0.8548   0.0893
  -8.250  -0.3153   0.04672   0.03894  -0.0944   0.8393   0.0915
  -8.000  -0.3071   0.04386   0.03563  -0.0937   0.8252   0.0942
  -7.750  -0.2933   0.04102   0.03227  -0.0933   0.8136   0.0971
  -7.500  -0.2737   0.03996   0.03115  -0.0924   0.7994   0.0996
  -7.250  -0.2549   0.03852   0.02948  -0.0915   0.7869   0.1028
  -7.000  -0.2339   0.03656   0.02700  -0.0910   0.7772   0.1077
  -6.750  -0.2142   0.03589   0.02635  -0.0899   0.7645   0.1114
  -6.500  -0.1916   0.03477   0.02498  -0.0891   0.7543   0.1168
  -6.250  -0.1697   0.03375   0.02375  -0.0882   0.7438   0.1226
  -6.000  -0.1478   0.03304   0.02289  -0.0872   0.7336   0.1300
  -5.750  -0.1234   0.03222   0.02193  -0.0866   0.7244   0.1387
  -5.500  -0.1017   0.03152   0.02101  -0.0855   0.7145   0.1501
  -5.250  -0.0771   0.03088   0.02025  -0.0849   0.7059   0.1636
  -5.000  -0.0556   0.03043   0.01978  -0.0838   0.6965   0.1784
  -4.750  -0.0316   0.02996   0.01923  -0.0830   0.6879   0.1964
  -4.500  -0.0091   0.02967   0.01886  -0.0821   0.6793   0.2149
  -4.250   0.0139   0.02944   0.01853  -0.0811   0.6706   0.2340
  -4.000   0.0388   0.02922   0.01821  -0.0804   0.6631   0.2537
  -3.750   0.0595   0.02918   0.01814  -0.0792   0.6539   0.2726
  -3.500   0.0870   0.02893   0.01784  -0.0788   0.6473   0.2948
  -3.250   0.1058   0.02898   0.01789  -0.0774   0.6379   0.3136
  -3.000   0.1340   0.02871   0.01751  -0.0772   0.6308   0.3330
  -2.750   0.1585   0.02860   0.01734  -0.0766   0.6228   0.3504
  -2.500   0.1834   0.02846   0.01715  -0.0760   0.6149   0.3691
  -2.250   0.2134   0.02810   0.01674  -0.0759   0.6091   0.3923
  -2.000   0.2299   0.02825   0.01700  -0.0742   0.6002   0.4145
  -1.750   0.2559   0.02803   0.01680  -0.0736   0.5937   0.4452
  -1.500   0.2777   0.02793   0.01683  -0.0724   0.5870   0.4818
  -1.250   0.2954   0.02795   0.01706  -0.0706   0.5792   0.5274
  -1.000   0.3207   0.02763   0.01699  -0.0694   0.5737   0.5978
  -0.750   0.3424   0.02767   0.01743  -0.0677   0.5665   0.6929
  -0.500   0.4008   0.02777   0.01774  -0.0721   0.5586   0.8399
  -0.250   0.4803   0.02785   0.01753  -0.0807   0.5521   0.9405
   0.000   0.5426   0.02849   0.01801  -0.0880   0.5427   1.0000
   0.250   0.5603   0.02872   0.01801  -0.0865   0.5375   1.0000
   0.500   0.5753   0.02914   0.01825  -0.0846   0.5320   1.0000
   0.750   0.5820   0.02989   0.01894  -0.0818   0.5250   1.0000
   1.000   0.6004   0.03025   0.01912  -0.0803   0.5199   1.0000
   1.250   0.6259   0.03041   0.01905  -0.0797   0.5162   1.0000
   1.500   0.6227   0.03168   0.02036  -0.0757   0.5086   1.0000
   1.750   0.6378   0.03224   0.02081  -0.0738   0.5033   1.0000
   2.000   0.6625   0.03246   0.02084  -0.0731   0.4995   1.0000
   2.250   0.6637   0.03366   0.02204  -0.0697   0.4932   1.0000
   2.500   0.6697   0.03469   0.02302  -0.0669   0.4872   1.0000
   2.750   0.6908   0.03512   0.02333  -0.0658   0.4833   1.0000
   3.000   0.7192   0.03532   0.02337  -0.0657   0.4805   1.0000
   3.250   0.6908   0.03800   0.02619  -0.0593   0.4724   1.0000
   3.500   0.7007   0.03901   0.02714  -0.0573   0.4678   1.0000
   3.750   0.7268   0.03930   0.02731  -0.0568   0.4647   1.0000
   4.000   0.6941   0.04237   0.03045  -0.0507   0.4572   1.0000
   4.250   0.6780   0.04485   0.03294  -0.0467   0.4508   1.0000
   4.500   0.6992   0.04547   0.03347  -0.0459   0.4479   1.0000
   4.750   0.7287   0.04565   0.03356  -0.0458   0.4459   1.0000
   5.250   0.6629   0.05504   0.04307  -0.0396   0.4299   1.0000
   6.250   0.6026   0.07273   0.06084  -0.0374   0.4038   1.0000
   6.500   0.6117   0.07478   0.06287  -0.0370   0.3999   1.0000
   6.750   0.6288   0.07612   0.06418  -0.0367   0.3974   1.0000
   7.000   0.6508   0.07698   0.06500  -0.0362   0.3955   1.0000
   7.250   0.6166   0.08342   0.07150  -0.0364   0.3868   1.0000
   7.500   0.6286   0.08520   0.07327  -0.0361   0.3828   1.0000
   7.750   0.6526   0.08574   0.07378  -0.0356   0.3800   1.0000
   8.000   0.6397   0.08976   0.07783  -0.0355   0.3715   1.0000
   8.250   0.6560   0.09077   0.07883  -0.0350   0.3659   1.0000
   8.500   0.6860   0.09043   0.07845  -0.0342   0.3627   1.0000
   8.750   0.6685   0.09493   0.08300  -0.0344   0.3524   1.0000
   9.000   0.6891   0.09556   0.08361  -0.0339   0.3481   1.0000
   9.250   0.7179   0.09531   0.08333  -0.0331   0.3454   1.0000
   9.500   0.6940   0.10087   0.08897  -0.0339   0.3346   1.0000
   9.750   0.7153   0.10146   0.08957  -0.0334   0.3308   1.0000
  10.250   0.7191   0.10702   0.09519  -0.0336   0.3166   1.0000
  10.500   0.7426   0.10726   0.09543  -0.0330   0.3133   1.0000
  11.000   0.7424   0.11365   0.10191  -0.0337   0.2988   1.0000
  11.250   0.7655   0.11398   0.10224  -0.0332   0.2962   1.0000
  11.500   0.7455   0.11981   0.10814  -0.0346   0.2852   1.0000
  11.750   0.7643   0.12064   0.10898  -0.0343   0.2817   1.0000
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