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GOE 526 AIRFOIL (goe526-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 526 AIRFOIL (goe526-il)
Reynolds number: 200,000
Max Cl/Cd: 69.41 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe526-il-200000-n5.txt
Download as CSV file: xf-goe526-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 526 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3542   0.09489   0.09100  -0.0463   1.0000   0.0390
 -10.000  -0.3628   0.09160   0.08776  -0.0463   0.9998   0.0395
  -9.500  -0.5400   0.03461   0.02932  -0.0936   0.9491   0.0413
  -9.250  -0.5289   0.03033   0.02435  -0.0947   0.9413   0.0421
  -9.000  -0.5079   0.02910   0.02302  -0.0944   0.9324   0.0426
  -8.750  -0.4816   0.02782   0.02161  -0.0951   0.9264   0.0432
  -8.500  -0.4588   0.02658   0.02020  -0.0950   0.9187   0.0438
  -8.250  -0.4351   0.02529   0.01869  -0.0949   0.9112   0.0445
  -8.000  -0.4102   0.02400   0.01715  -0.0950   0.9045   0.0453
  -7.750  -0.3875   0.02286   0.01576  -0.0944   0.8959   0.0462
  -7.500  -0.3602   0.02173   0.01433  -0.0946   0.8903   0.0474
  -7.250  -0.3377   0.02090   0.01336  -0.0938   0.8817   0.0483
  -7.000  -0.3105   0.02023   0.01265  -0.0938   0.8754   0.0492
  -6.750  -0.2852   0.01963   0.01197  -0.0934   0.8682   0.0502
  -6.500  -0.2596   0.01899   0.01121  -0.0930   0.8611   0.0513
  -6.000  -0.2081   0.01778   0.00971  -0.0921   0.8483   0.0539
  -5.750  -0.1820   0.01723   0.00910  -0.0917   0.8420   0.0554
  -5.500  -0.1555   0.01684   0.00868  -0.0914   0.8364   0.0571
  -5.250  -0.1307   0.01647   0.00826  -0.0908   0.8297   0.0591
  -5.000  -0.1040   0.01606   0.00773  -0.0904   0.8242   0.0613
  -4.750  -0.0780   0.01564   0.00728  -0.0899   0.8188   0.0633
  -4.500  -0.0532   0.01534   0.00697  -0.0892   0.8117   0.0656
  -4.250  -0.0264   0.01504   0.00658  -0.0888   0.8053   0.0689
  -4.000  -0.0015   0.01474   0.00626  -0.0881   0.7972   0.0722
  -3.750   0.0244   0.01449   0.00598  -0.0875   0.7890   0.0760
  -3.500   0.0501   0.01425   0.00567  -0.0868   0.7811   0.0804
  -3.250   0.0753   0.01402   0.00545  -0.0861   0.7725   0.0853
  -3.000   0.1018   0.01382   0.00520  -0.0856   0.7658   0.0913
  -2.750   0.1267   0.01365   0.00508  -0.0849   0.7585   0.0982
  -2.500   0.1531   0.01350   0.00491  -0.0844   0.7524   0.1061
  -2.250   0.1793   0.01338   0.00477  -0.0839   0.7464   0.1150
  -2.000   0.2046   0.01325   0.00470  -0.0833   0.7393   0.1242
  -1.750   0.2312   0.01315   0.00455  -0.0828   0.7334   0.1338
  -1.500   0.2568   0.01305   0.00448  -0.0822   0.7266   0.1440
  -1.250   0.2822   0.01294   0.00439  -0.0815   0.7196   0.1536
  -0.750   0.3333   0.01274   0.00422  -0.0803   0.7057   0.1749
  -0.500   0.3591   0.01264   0.00412  -0.0797   0.6986   0.1868
  -0.250   0.3842   0.01255   0.00408  -0.0789   0.6911   0.2011
   0.000   0.4091   0.01244   0.00403  -0.0782   0.6832   0.2194
   0.250   0.4336   0.01230   0.00398  -0.0774   0.6752   0.2462
   0.500   0.4571   0.01211   0.00396  -0.0764   0.6660   0.2939
   0.750   0.4776   0.01168   0.00396  -0.0750   0.6572   0.4202
   1.250   0.5971   0.01078   0.00439  -0.0870   0.6343   0.9681
   1.500   0.6492   0.01089   0.00438  -0.0919   0.6169   0.9866
   1.750   0.7010   0.01096   0.00431  -0.0969   0.5963   0.9994
   2.000   0.7239   0.01107   0.00432  -0.0958   0.5790   1.0000
   2.250   0.7443   0.01120   0.00435  -0.0941   0.5622   1.0000
   2.500   0.7643   0.01135   0.00440  -0.0925   0.5455   1.0000
   2.750   0.7838   0.01152   0.00447  -0.0907   0.5280   1.0000
   3.250   0.8206   0.01197   0.00467  -0.0868   0.4910   1.0000
   3.500   0.8392   0.01221   0.00481  -0.0849   0.4761   1.0000
   3.750   0.8580   0.01245   0.00498  -0.0831   0.4628   1.0000
   4.000   0.8768   0.01270   0.00515  -0.0812   0.4513   1.0000
   4.500   0.9143   0.01321   0.00555  -0.0776   0.4303   1.0000
   4.750   0.9329   0.01349   0.00576  -0.0758   0.4210   1.0000
   5.000   0.9522   0.01373   0.00599  -0.0741   0.4125   1.0000
   5.250   0.9708   0.01402   0.00623  -0.0723   0.4044   1.0000
   5.500   0.9898   0.01426   0.00647  -0.0705   0.3954   1.0000
   5.750   1.0079   0.01456   0.00673  -0.0687   0.3873   1.0000
   6.000   1.0264   0.01481   0.00699  -0.0669   0.3777   1.0000
   6.250   1.0434   0.01511   0.00726  -0.0648   0.3679   1.0000
   6.500   1.0602   0.01539   0.00753  -0.0627   0.3572   1.0000
   6.750   1.0770   0.01568   0.00782  -0.0607   0.3470   1.0000
   7.000   1.0917   0.01602   0.00812  -0.0583   0.3363   1.0000
   7.250   1.1069   0.01632   0.00843  -0.0559   0.3233   1.0000
   7.500   1.1202   0.01665   0.00876  -0.0533   0.3106   1.0000
   7.750   1.1317   0.01701   0.00909  -0.0503   0.2977   1.0000
   8.000   1.1426   0.01741   0.00947  -0.0474   0.2831   1.0000
   8.250   1.1536   0.01787   0.00988  -0.0445   0.2668   1.0000
   8.500   1.1632   0.01841   0.01037  -0.0416   0.2471   1.0000
   8.750   1.1709   0.01909   0.01095  -0.0386   0.2261   1.0000
   9.000   1.1788   0.01984   0.01161  -0.0357   0.2077   1.0000
   9.250   1.1864   0.02066   0.01235  -0.0330   0.1928   1.0000
   9.750   1.2043   0.02235   0.01398  -0.0282   0.1733   1.0000
  10.000   1.2117   0.02334   0.01493  -0.0258   0.1656   1.0000
  10.250   1.2232   0.02415   0.01579  -0.0240   0.1585   1.0000
  10.500   1.2311   0.02520   0.01683  -0.0219   0.1520   1.0000
  10.750   1.2424   0.02609   0.01778  -0.0203   0.1457   1.0000
  11.000   1.2518   0.02713   0.01885  -0.0185   0.1388   1.0000
  11.250   1.2611   0.02820   0.01996  -0.0169   0.1326   1.0000
  11.500   1.2711   0.02927   0.02108  -0.0155   0.1251   1.0000
  11.750   1.2797   0.03047   0.02230  -0.0140   0.1185   1.0000
  12.000   1.2877   0.03175   0.02362  -0.0126   0.1111   1.0000
  12.250   1.2951   0.03311   0.02501  -0.0112   0.1050   1.0000
  12.500   1.3011   0.03463   0.02654  -0.0099   0.0992   1.0000
  12.750   1.3066   0.03622   0.02817  -0.0087   0.0946   1.0000
  13.000   1.3113   0.03793   0.02990  -0.0075   0.0901   1.0000
  13.250   1.3135   0.03991   0.03190  -0.0064   0.0867   1.0000
  13.500   1.3185   0.04170   0.03377  -0.0054   0.0836   1.0000
  13.750   1.3219   0.04368   0.03582  -0.0046   0.0807   1.0000
  14.000   1.3233   0.04591   0.03810  -0.0038   0.0783   1.0000
  14.250   1.3230   0.04838   0.04060  -0.0031   0.0761   1.0000
  14.500   1.3274   0.05045   0.04278  -0.0026   0.0738   1.0000
  14.750   1.3300   0.05276   0.04519  -0.0022   0.0716   1.0000
  15.000   1.3307   0.05533   0.04783  -0.0019   0.0697   1.0000
  15.250   1.3295   0.05818   0.05073  -0.0017   0.0679   1.0000
  15.500   1.3296   0.06095   0.05356  -0.0017   0.0663   1.0000
  15.750   1.3321   0.06352   0.05626  -0.0017   0.0645   1.0000
  16.000   1.3332   0.06630   0.05914  -0.0018   0.0628   1.0000
  16.250   1.3331   0.06930   0.06223  -0.0022   0.0611   1.0000
  16.500   1.3315   0.07255   0.06553  -0.0026   0.0597   1.0000
  16.750   1.3294   0.07585   0.06887  -0.0031   0.0583   1.0000
  17.000   1.3303   0.07890   0.07207  -0.0037   0.0568   1.0000
  17.250   1.3301   0.08213   0.07542  -0.0044   0.0553   1.0000
  17.500   1.3288   0.08558   0.07896  -0.0052   0.0538   1.0000
  17.750   1.3271   0.08909   0.08255  -0.0062   0.0526   1.0000
  18.000   1.3244   0.09274   0.08625  -0.0072   0.0516   1.0000
  18.250   1.3223   0.09637   0.08997  -0.0083   0.0503   1.0000
  18.500   1.3209   0.09999   0.09373  -0.0095   0.0492   1.0000
  18.750   1.3184   0.10380   0.09765  -0.0108   0.0479   1.0000
  19.000   1.3153   0.10776   0.10172  -0.0124   0.0467   1.0000
  19.250   1.3122   0.11169   0.10572  -0.0139   0.0458   1.0000
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