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GOE 534 AIRFOIL (goe534-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 534 AIRFOIL (goe534-il)
Reynolds number: 50,000
Max Cl/Cd: 32.49 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe534-il-50000-n5.txt
Download as CSV file: xf-goe534-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 534 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2415   0.10281   0.09552  -0.0323   1.0000   0.0961
  -9.000  -0.2424   0.09982   0.09261  -0.0327   1.0000   0.0956
  -8.750  -0.2452   0.09678   0.08968  -0.0331   1.0000   0.0950
  -8.500  -0.2500   0.09384   0.08685  -0.0332   1.0000   0.0945
  -8.250  -0.2571   0.09115   0.08429  -0.0330   1.0000   0.0944
  -8.000  -0.2673   0.08889   0.08218  -0.0321   1.0000   0.0949
  -7.750  -0.2842   0.08714   0.08061  -0.0301   1.0000   0.0954
  -7.500  -0.3082   0.08592   0.07956  -0.0271   1.0000   0.0953
  -7.250  -0.2981   0.08079   0.07444  -0.0340   0.9858   0.0971
  -7.000  -0.2827   0.07289   0.06647  -0.0460   0.9677   0.0987
  -6.750  -0.2704   0.06271   0.05613  -0.0602   0.9491   0.1010
  -6.500  -0.2363   0.06105   0.05445  -0.0632   0.9369   0.1048
  -6.250  -0.2208   0.04633   0.03890  -0.0834   0.9200   0.1123
  -6.000  -0.1875   0.04579   0.03844  -0.0842   0.9066   0.1167
  -5.750  -0.1565   0.04040   0.03242  -0.0914   0.8933   0.1252
  -5.500  -0.1184   0.03915   0.03109  -0.0938   0.8821   0.1330
  -5.250  -0.0884   0.03725   0.02893  -0.0958   0.8671   0.1404
  -5.000  -0.0561   0.03564   0.02707  -0.0976   0.8533   0.1476
  -4.750  -0.0204   0.03355   0.02459  -0.0999   0.8414   0.1534
  -4.500   0.0087   0.03256   0.02349  -0.1002   0.8259   0.1577
  -4.250   0.0385   0.03117   0.02177  -0.1009   0.8112   0.1620
  -4.000   0.0706   0.02979   0.01998  -0.1017   0.7979   0.1670
  -3.750   0.0996   0.02910   0.01924  -0.1015   0.7832   0.1707
  -3.500   0.1267   0.02840   0.01839  -0.1010   0.7678   0.1744
  -3.250   0.1554   0.02766   0.01739  -0.1008   0.7536   0.1796
  -3.000   0.1848   0.02705   0.01662  -0.1006   0.7402   0.1853
  -2.750   0.2105   0.02670   0.01624  -0.0999   0.7247   0.1909
  -2.500   0.2387   0.02623   0.01556  -0.0995   0.7107   0.1982
  -2.250   0.2673   0.02583   0.01511  -0.0990   0.6984   0.2057
  -2.000   0.2930   0.02559   0.01475  -0.0983   0.6834   0.2174
  -1.750   0.3201   0.02541   0.01460  -0.0977   0.6700   0.2315
  -1.500   0.3494   0.02518   0.01431  -0.0973   0.6582   0.2519
  -1.250   0.3752   0.02513   0.01429  -0.0966   0.6441   0.2759
  -1.000   0.4017   0.02514   0.01433  -0.0958   0.6316   0.3021
  -0.750   0.4293   0.02517   0.01427  -0.0951   0.6201   0.3320
  -0.500   0.4542   0.02534   0.01444  -0.0941   0.6069   0.3576
  -0.250   0.4806   0.02544   0.01449  -0.0932   0.5956   0.3829
   0.000   0.5058   0.02566   0.01464  -0.0922   0.5838   0.4152
   0.250   0.5293   0.02589   0.01495  -0.0909   0.5719   0.4453
   0.500   0.5563   0.02594   0.01488  -0.0899   0.5618   0.4753
   0.750   0.5805   0.02609   0.01504  -0.0890   0.5494   0.4967
   1.000   0.6082   0.02609   0.01493  -0.0884   0.5391   0.5164
   1.250   0.6341   0.02619   0.01499  -0.0878   0.5276   0.5351
   1.500   0.6608   0.02628   0.01503  -0.0872   0.5172   0.5549
   1.750   0.6875   0.02636   0.01508  -0.0866   0.5066   0.5757
   2.000   0.7132   0.02649   0.01524  -0.0860   0.4961   0.5992
   2.250   0.7394   0.02654   0.01532  -0.0854   0.4861   0.6262
   3.000   0.8203   0.02670   0.01600  -0.0843   0.4556   1.0000
   3.250   0.8470   0.02716   0.01624  -0.0840   0.4463   1.0000
   3.500   0.8710   0.02778   0.01675  -0.0834   0.4366   1.0000
   3.750   0.8961   0.02827   0.01709  -0.0828   0.4274   1.0000
   4.000   0.9195   0.02889   0.01761  -0.0820   0.4183   1.0000
   4.250   0.9429   0.02947   0.01811  -0.0812   0.4093   1.0000
   4.500   0.9668   0.03005   0.01858  -0.0805   0.4012   1.0000
   4.750   0.9878   0.03077   0.01928  -0.0795   0.3920   1.0000
   5.000   1.0136   0.03120   0.01954  -0.0788   0.3850   1.0000
   5.250   1.0310   0.03217   0.02059  -0.0776   0.3757   1.0000
   5.500   1.0562   0.03262   0.02090  -0.0769   0.3690   1.0000
   5.750   1.0732   0.03364   0.02199  -0.0756   0.3606   1.0000
   6.000   1.0948   0.03430   0.02260  -0.0746   0.3534   1.0000
   6.250   1.1163   0.03501   0.02326  -0.0736   0.3469   1.0000
   6.500   1.1313   0.03615   0.02449  -0.0722   0.3392   1.0000
   6.750   1.1554   0.03662   0.02486  -0.0714   0.3333   1.0000
   7.000   1.1682   0.03791   0.02625  -0.0698   0.3262   1.0000
   7.250   1.1843   0.03893   0.02731  -0.0685   0.3197   1.0000
   7.500   1.2105   0.03928   0.02753  -0.0679   0.3147   1.0000
   7.750   1.2136   0.04116   0.02962  -0.0657   0.3078   1.0000
   8.000   1.2280   0.04222   0.03071  -0.0642   0.3018   1.0000
   8.250   1.2555   0.04250   0.03087  -0.0637   0.2972   1.0000
   8.500   1.2480   0.04500   0.03363  -0.0608   0.2911   1.0000
   8.750   1.2542   0.04652   0.03522  -0.0589   0.2855   1.0000
   9.000   1.2808   0.04678   0.03537  -0.0583   0.2809   1.0000
   9.250   1.2673   0.04951   0.03828  -0.0552   0.2761   1.0000
   9.500   1.2426   0.05328   0.04228  -0.0523   0.2710   1.0000
   9.750   1.2528   0.05466   0.04366  -0.0511   0.2664   1.0000
  10.000   1.2925   0.05385   0.04270  -0.0507   0.2624   1.0000
  10.250   1.1018   0.07790   0.06747  -0.0552   0.2514   1.0000
  10.500   1.1280   0.07735   0.06689  -0.0537   0.2485   1.0000
  10.750   1.1795   0.07339   0.06284  -0.0507   0.2467   1.0000
  11.000   1.0378   0.09979   0.08955  -0.0623   0.2311   1.0000
  11.250   1.0663   0.09840   0.08815  -0.0603   0.2293   1.0000
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