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GOE 257 AIRFOIL (goe257-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 257 AIRFOIL (goe257-il)
Reynolds number: 200,000
Max Cl/Cd: 74.88 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe257-il-200000.txt
Download as CSV file: xf-goe257-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3951   0.09878   0.09539  -0.0147   1.0000   0.0299
  -8.000  -0.3916   0.09548   0.09213  -0.0166   1.0000   0.0307
  -7.750  -0.3903   0.09237   0.08907  -0.0191   1.0000   0.0317
  -7.500  -0.3824   0.08890   0.08562  -0.0288   1.0000   0.0328
  -7.250  -0.3666   0.08473   0.08139  -0.0381   1.0000   0.0332
  -7.000  -0.3581   0.07921   0.07587  -0.0410   1.0000   0.0335
  -6.750  -0.3550   0.07518   0.07191  -0.0382   1.0000   0.0342
  -6.500  -0.3468   0.07207   0.06883  -0.0375   1.0000   0.0349
  -6.250  -0.3369   0.06893   0.06570  -0.0382   1.0000   0.0359
  -6.000  -0.3259   0.06571   0.06247  -0.0396   1.0000   0.0371
  -5.750  -0.3137   0.06242   0.05913  -0.0413   1.0000   0.0386
  -5.500  -0.2985   0.05907   0.05570  -0.0435   1.0000   0.0409
  -5.250  -0.2655   0.05345   0.04971  -0.0506   0.9981   0.0439
  -5.000  -0.2355   0.04964   0.04597  -0.0542   0.9928   0.0463
  -4.750  -0.1932   0.04570   0.04186  -0.0601   0.9864   0.0507
  -4.500  -0.1435   0.04053   0.03621  -0.0673   0.9806   0.0570
  -4.250  -0.1075   0.03767   0.03332  -0.0711   0.9716   0.0613
  -4.000  -0.0663   0.03439   0.02966  -0.0753   0.9598   0.0713
  -3.500   0.0007   0.02973   0.02461  -0.0794   0.9277   0.0874
  -3.250   0.0296   0.02802   0.02255  -0.0799   0.9078   0.0998
  -3.000   0.0556   0.02663   0.02091  -0.0798   0.8872   0.1136
  -2.750   0.0796   0.02509   0.01927  -0.0795   0.8683   0.1293
  -2.500   0.1043   0.02373   0.01780  -0.0793   0.8504   0.1466
  -2.250   0.1295   0.02256   0.01647  -0.0793   0.8336   0.1745
  -1.500   0.2295   0.01793   0.01017  -0.0768   0.7951   0.0800
  -1.250   0.2587   0.01664   0.00862  -0.0765   0.7832   0.0731
  -1.000   0.2877   0.01638   0.00810  -0.0760   0.7717   0.0678
  -0.750   0.3157   0.01542   0.00704  -0.0757   0.7612   0.0658
  -0.500   0.3435   0.01484   0.00636  -0.0754   0.7509   0.0646
  -0.250   0.3718   0.01437   0.00585  -0.0753   0.7399   0.0641
   0.000   0.3999   0.01404   0.00548  -0.0752   0.7299   0.0644
   0.250   0.4277   0.01383   0.00520  -0.0751   0.7198   0.0657
   0.500   0.4558   0.01370   0.00503  -0.0751   0.7083   0.0687
   0.750   0.4840   0.01352   0.00480  -0.0751   0.6962   0.0714
   1.000   0.5122   0.01347   0.00468  -0.0751   0.6842   0.0754
   1.250   0.5403   0.01344   0.00460  -0.0750   0.6728   0.0850
   1.500   0.5640   0.01117   0.00449  -0.0741   0.6627   1.0000
   1.750   0.5923   0.01130   0.00449  -0.0741   0.6510   1.0000
   2.000   0.6203   0.01144   0.00451  -0.0741   0.6392   1.0000
   2.250   0.6482   0.01157   0.00454  -0.0741   0.6277   1.0000
   2.500   0.6761   0.01172   0.00458  -0.0740   0.6168   1.0000
   2.750   0.7040   0.01183   0.00464  -0.0740   0.6051   1.0000
   3.000   0.7319   0.01195   0.00472  -0.0740   0.5928   1.0000
   3.250   0.7597   0.01207   0.00481  -0.0741   0.5811   1.0000
   3.500   0.7875   0.01221   0.00492  -0.0741   0.5704   1.0000
   3.750   0.8152   0.01234   0.00500  -0.0741   0.5591   1.0000
   4.000   0.8428   0.01246   0.00511  -0.0740   0.5461   1.0000
   4.250   0.8703   0.01258   0.00525  -0.0740   0.5326   1.0000
   4.500   0.8978   0.01273   0.00540  -0.0740   0.5197   1.0000
   4.750   0.9252   0.01290   0.00559  -0.0740   0.5073   1.0000
   5.000   0.9524   0.01309   0.00579  -0.0740   0.4944   1.0000
   5.250   0.9794   0.01330   0.00602  -0.0739   0.4803   1.0000
   5.500   1.0056   0.01353   0.00621  -0.0737   0.4611   1.0000
   5.750   1.0315   0.01379   0.00644  -0.0734   0.4379   1.0000
   6.000   1.0568   0.01413   0.00671  -0.0731   0.4130   1.0000
   6.250   1.0820   0.01445   0.00703  -0.0728   0.3831   1.0000
   6.500   1.1075   0.01479   0.00737  -0.0726   0.3542   1.0000
   6.750   1.1318   0.01523   0.00773  -0.0723   0.3127   1.0000
   7.000   1.1534   0.01605   0.00826  -0.0717   0.2615   1.0000
   7.250   1.1744   0.01700   0.00904  -0.0710   0.2229   1.0000
   7.500   1.1912   0.01850   0.01006  -0.0699   0.1307   1.0000
   7.750   1.1974   0.02143   0.01238  -0.0673   0.0455   1.0000
   8.250   1.2326   0.02381   0.01499  -0.0644   0.0334   1.0000
   8.500   1.2482   0.02500   0.01632  -0.0628   0.0310   1.0000
   8.750   1.2599   0.02644   0.01784  -0.0607   0.0294   1.0000
   9.000   1.2641   0.02844   0.01991  -0.0576   0.0281   1.0000
   9.250   1.2735   0.02992   0.02148  -0.0551   0.0271   1.0000
   9.500   1.2831   0.03131   0.02298  -0.0528   0.0259   1.0000
   9.750   1.2893   0.03292   0.02468  -0.0499   0.0251   1.0000
  10.000   1.2971   0.03469   0.02653  -0.0473   0.0246   1.0000
  10.250   1.3080   0.03658   0.02854  -0.0452   0.0241   1.0000
  10.500   1.3226   0.03862   0.03069  -0.0435   0.0238   1.0000
  10.750   1.3418   0.04096   0.03318  -0.0424   0.0236   1.0000
  11.000   1.3652   0.04397   0.03642  -0.0419   0.0239   1.0000
  11.250   1.3801   0.04702   0.03974  -0.0405   0.0239   1.0000
  11.500   1.3864   0.04969   0.04264  -0.0383   0.0236   1.0000
  11.750   1.3891   0.05226   0.04542  -0.0360   0.0231   1.0000
  12.000   1.3864   0.05561   0.04909  -0.0334   0.0233   1.0000
  12.250   1.3764   0.06020   0.05411  -0.0307   0.0243   1.0000
  12.500   1.3642   0.06468   0.05891  -0.0286   0.0251   1.0000
  12.750   1.3502   0.06929   0.06379  -0.0271   0.0258   1.0000
  13.000   1.3350   0.07423   0.06896  -0.0264   0.0264   1.0000
  13.250   1.3196   0.07991   0.07484  -0.0263   0.0271   1.0000
  13.500   1.1623   0.07658   0.07175  -0.0142   0.0251   1.0000
  13.750   1.1374   0.08203   0.07740  -0.0147   0.0254   1.0000
  14.000   1.1106   0.08743   0.08300  -0.0155   0.0256   1.0000
  14.250   1.0810   0.09266   0.08841  -0.0167   0.0258   1.0000
  14.500   1.0490   0.09760   0.09352  -0.0181   0.0261   1.0000
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