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GOE 257 AIRFOIL (goe257-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 257 AIRFOIL (goe257-il)
Reynolds number: 50,000
Max Cl/Cd: 39.84 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe257-il-50000-n5.txt
Download as CSV file: xf-goe257-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 257 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3900   0.10657   0.10000  -0.0182   1.0000   0.0961
  -8.000  -0.3968   0.10484   0.09840  -0.0217   1.0000   0.0990
  -7.750  -0.3992   0.10301   0.09664  -0.0297   1.0000   0.1001
  -7.500  -0.3838   0.09691   0.09058  -0.0233   1.0000   0.1037
  -7.250  -0.3767   0.09357   0.08728  -0.0243   1.0000   0.1089
  -7.000  -0.3748   0.09150   0.08523  -0.0341   1.0000   0.1143
  -6.750  -0.3650   0.08671   0.08050  -0.0289   1.0000   0.1196
  -6.500  -0.3573   0.08451   0.07823  -0.0380   1.0000   0.1289
  -6.000  -0.3379   0.07726   0.07104  -0.0402   1.0000   0.1442
  -5.750  -0.3305   0.07329   0.06720  -0.0363   1.0000   0.1483
  -5.500  -0.3186   0.07020   0.06406  -0.0397   1.0000   0.1603
  -5.250  -0.3081   0.06734   0.06121  -0.0395   1.0000   0.1714
  -4.750  -0.2924   0.06178   0.05574  -0.0385   1.0000   0.2068
  -4.250  -0.2208   0.05186   0.04471  -0.0508   0.9996   0.0988
  -4.000  -0.1763   0.04674   0.03916  -0.0561   0.9907   0.0816
  -3.750  -0.1322   0.04306   0.03501  -0.0613   0.9812   0.0814
  -3.500  -0.0880   0.03960   0.03106  -0.0659   0.9715   0.0784
  -3.250  -0.0404   0.03635   0.02712  -0.0704   0.9620   0.0743
  -3.000   0.0070   0.03396   0.02390  -0.0741   0.9513   0.0717
  -2.750   0.0480   0.03174   0.02143  -0.0773   0.9394   0.0736
  -2.500   0.0880   0.03007   0.01946  -0.0799   0.9269   0.0765
  -2.250   0.1273   0.02853   0.01751  -0.0819   0.9145   0.0762
  -2.000   0.1649   0.02723   0.01587  -0.0835   0.9022   0.0759
  -1.750   0.2008   0.02614   0.01451  -0.0847   0.8903   0.0761
  -1.500   0.2341   0.02526   0.01341  -0.0852   0.8776   0.0767
  -1.250   0.2663   0.02456   0.01248  -0.0856   0.8644   0.0777
  -1.000   0.2973   0.02397   0.01172  -0.0858   0.8511   0.0792
  -0.750   0.3273   0.02353   0.01110  -0.0859   0.8381   0.0830
  -0.500   0.3567   0.02311   0.01058  -0.0861   0.8254   0.0889
  -0.250   0.3860   0.02277   0.01013  -0.0862   0.8131   0.0950
   0.000   0.4154   0.02251   0.00973  -0.0861   0.8012   0.1008
   0.250   0.4449   0.02221   0.00936  -0.0861   0.7902   0.1126
   0.500   0.4680   0.02029   0.00936  -0.0857   0.7789   0.6183
   1.000   0.5250   0.02007   0.00899  -0.0847   0.7555   1.0000
   1.250   0.5528   0.02031   0.00899  -0.0844   0.7452   1.0000
   1.500   0.5799   0.02061   0.00912  -0.0841   0.7338   1.0000
   1.750   0.6067   0.02096   0.00934  -0.0839   0.7225   1.0000
   2.000   0.6337   0.02131   0.00958  -0.0837   0.7119   1.0000
   2.250   0.6616   0.02163   0.00979  -0.0835   0.7023   1.0000
   2.500   0.6881   0.02207   0.01021  -0.0834   0.6907   1.0000
   2.750   0.7147   0.02250   0.01061  -0.0833   0.6796   1.0000
   3.000   0.7412   0.02288   0.01096  -0.0830   0.6682   1.0000
   3.250   0.7675   0.02321   0.01127  -0.0825   0.6560   1.0000
   3.500   0.7931   0.02350   0.01154  -0.0818   0.6420   1.0000
   3.750   0.8180   0.02376   0.01181  -0.0810   0.6264   1.0000
   4.000   0.8428   0.02402   0.01209  -0.0803   0.6107   1.0000
   4.250   0.8682   0.02429   0.01242  -0.0797   0.5972   1.0000
   4.500   0.8935   0.02466   0.01289  -0.0792   0.5845   1.0000
   4.750   0.9184   0.02506   0.01340  -0.0788   0.5715   1.0000
   5.000   0.9433   0.02543   0.01393  -0.0782   0.5585   1.0000
   5.250   0.9681   0.02581   0.01445  -0.0777   0.5455   1.0000
   5.500   0.9929   0.02618   0.01495  -0.0771   0.5321   1.0000
   5.750   1.0174   0.02654   0.01547  -0.0765   0.5185   1.0000
   6.000   1.0419   0.02692   0.01604  -0.0758   0.5046   1.0000
   6.250   1.0661   0.02732   0.01661  -0.0751   0.4903   1.0000
   6.500   1.0902   0.02774   0.01720  -0.0743   0.4755   1.0000
   6.750   1.1139   0.02822   0.01786  -0.0735   0.4603   1.0000
   7.000   1.1373   0.02874   0.01861  -0.0726   0.4444   1.0000
   7.250   1.1596   0.02921   0.01924  -0.0715   0.4258   1.0000
   7.500   1.1777   0.02956   0.01967  -0.0697   0.3971   1.0000
   7.750   1.1929   0.02999   0.02013  -0.0676   0.3629   1.0000
   8.000   1.2082   0.03069   0.02102  -0.0659   0.3315   1.0000
   8.250   1.2174   0.03159   0.02187  -0.0634   0.2827   1.0000
   8.500   1.2208   0.03322   0.02312  -0.0605   0.2318   1.0000
   8.750   1.2209   0.03547   0.02517  -0.0577   0.1641   1.0000
   9.000   1.2055   0.03910   0.02795  -0.0541   0.0822   1.0000
   9.250   1.1932   0.04236   0.03100  -0.0506   0.0683   1.0000
   9.500   1.1843   0.04565   0.03435  -0.0481   0.0606   1.0000
   9.750   1.1760   0.04919   0.03796  -0.0464   0.0562   1.0000
  10.000   1.1720   0.05252   0.04152  -0.0453   0.0525   1.0000
  10.250   1.1673   0.05610   0.04529  -0.0446   0.0494   1.0000
  10.500   1.1617   0.05990   0.04923  -0.0442   0.0469   1.0000
  10.750   1.1544   0.06396   0.05338  -0.0439   0.0449   1.0000
  11.000   1.1550   0.06716   0.05679  -0.0435   0.0423   1.0000
  11.250   1.1547   0.07046   0.06029  -0.0431   0.0399   1.0000
  11.500   1.1547   0.07373   0.06376  -0.0427   0.0381   1.0000
  11.750   1.1561   0.07678   0.06690  -0.0419   0.0367   1.0000
  12.000   1.1608   0.07933   0.06947  -0.0406   0.0355   1.0000
  12.250   1.1722   0.08137   0.07180  -0.0388   0.0344   1.0000
  12.500   1.1816   0.08389   0.07461  -0.0375   0.0331   1.0000
  12.750   1.1865   0.08705   0.07803  -0.0370   0.0318   1.0000
  13.000   1.1878   0.09070   0.08192  -0.0370   0.0307   1.0000
  13.250   1.1866   0.09469   0.08611  -0.0375   0.0298   1.0000
  13.500   1.1843   0.09891   0.09051  -0.0382   0.0292   1.0000
  13.750   1.1807   0.10341   0.09520  -0.0392   0.0287   1.0000
  14.000   1.1750   0.10842   0.10041  -0.0407   0.0284   1.0000
  14.250   1.1661   0.11415   0.10637  -0.0430   0.0284   1.0000
  14.500   1.1543   0.12069   0.11315  -0.0462   0.0284   1.0000
  14.750   1.1397   0.12823   0.12092  -0.0506   0.0286   1.0000
  15.000   1.1225   0.13709   0.13003  -0.0562   0.0289   1.0000
  15.250   1.1031   0.14760   0.14076  -0.0631   0.0295   1.0000
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