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WORTMANN FX 60-126 AIRFOIL (fx60126-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 60-126 AIRFOIL (fx60126-il)
Reynolds number: 50,000
Max Cl/Cd: 34.37 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx60126-il-50000.txt
Download as CSV file: xf-fx60126-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 60-126 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3455   0.12197   0.11494  -0.0301   1.0000   0.2415
  -9.750  -0.3124   0.11503   0.10796  -0.0285   1.0000   0.2491
  -9.500  -0.3261   0.11426   0.10731  -0.0291   1.0000   0.2562
  -9.250  -0.3100   0.10958   0.10266  -0.0283   1.0000   0.2619
  -9.000  -0.3182   0.10812   0.10131  -0.0281   1.0000   0.2712
  -8.750  -0.3180   0.10490   0.09818  -0.0278   1.0000   0.2744
  -8.500  -0.3086   0.10115   0.09445  -0.0271   1.0000   0.2781
  -8.250  -0.4060   0.08695   0.08065  -0.0422   1.0000   0.1378
  -8.000  -0.4116   0.08369   0.07747  -0.0408   1.0000   0.1337
  -7.750  -0.4279   0.08033   0.07426  -0.0395   1.0000   0.1294
  -7.500  -0.4689   0.07179   0.06587  -0.0459   1.0000   0.1187
  -7.250  -0.5209   0.05890   0.05247  -0.0602   1.0000   0.1084
  -7.000  -0.5175   0.05416   0.04755  -0.0617   1.0000   0.1073
  -6.750  -0.5092   0.04890   0.04187  -0.0644   1.0000   0.1066
  -6.500  -0.4931   0.04381   0.03615  -0.0676   1.0000   0.1075
  -6.250  -0.4741   0.04024   0.03230  -0.0688   1.0000   0.1121
  -6.000  -0.4518   0.03735   0.02906  -0.0697   1.0000   0.1195
  -5.750  -0.4284   0.03467   0.02614  -0.0703   1.0000   0.1292
  -5.500  -0.4033   0.03234   0.02360  -0.0709   1.0000   0.1466
  -5.250  -0.3788   0.03043   0.02171  -0.0712   1.0000   0.1730
  -5.000  -0.3535   0.02893   0.02027  -0.0715   1.0000   0.2130
  -4.750  -0.3307   0.02810   0.01971  -0.0710   1.0000   0.2588
  -4.500  -0.3100   0.02777   0.01967  -0.0695   1.0000   0.3061
  -4.250  -0.2935   0.02830   0.02047  -0.0667   1.0000   0.3537
  -4.000  -0.2790   0.02916   0.02146  -0.0635   1.0000   0.3983
  -3.750  -0.2673   0.03003   0.02245  -0.0595   1.0000   0.4322
  -3.500  -0.2541   0.03060   0.02305  -0.0562   1.0000   0.4638
  -3.250  -0.2398   0.03100   0.02340  -0.0535   1.0000   0.4937
  -3.000  -0.2246   0.03130   0.02362  -0.0512   1.0000   0.5231
  -2.750  -0.2149   0.03166   0.02403  -0.0475   1.0000   0.5446
  -2.500  -0.1990   0.03177   0.02405  -0.0458   1.0000   0.5719
  -2.250  -0.1870   0.03187   0.02412  -0.0431   1.0000   0.5932
  -2.000  -0.1676   0.03181   0.02393  -0.0428   1.0000   0.6182
  -1.750  -0.1536   0.03177   0.02384  -0.0411   1.0000   0.6369
  -1.500  -0.1382   0.03174   0.02376  -0.0398   1.0000   0.6563
  -1.250  -0.1203   0.03176   0.02368  -0.0394   0.9998   0.6767
  -1.000  -0.0797   0.03225   0.02404  -0.0427   0.9873   0.7008
  -0.750  -0.0401   0.03267   0.02434  -0.0460   0.9747   0.7226
  -0.500  -0.0006   0.03306   0.02459  -0.0493   0.9614   0.7449
  -0.250   0.0339   0.03339   0.02484  -0.0513   0.9479   0.7661
   0.000   0.0712   0.03374   0.02508  -0.0541   0.9345   0.7870
   0.250   0.1082   0.03407   0.02534  -0.0567   0.9213   0.8075
   0.500   0.1442   0.03437   0.02560  -0.0588   0.9089   0.8294
   0.750   0.1709   0.03456   0.02577  -0.0597   0.8955   0.8524
   1.000   0.1950   0.03472   0.02595  -0.0599   0.8824   0.8777
   1.250   0.2227   0.03489   0.02619  -0.0607   0.8692   0.9106
   1.500   0.2686   0.03512   0.02649  -0.0655   0.8537   1.0000
   1.750   0.3217   0.03594   0.02719  -0.0724   0.8388   1.0000
   2.000   0.3729   0.03677   0.02790  -0.0787   0.8243   1.0000
   2.250   0.4222   0.03759   0.02863  -0.0843   0.8103   1.0000
   2.500   0.4723   0.03836   0.02932  -0.0895   0.7972   1.0000
   2.750   0.5178   0.03909   0.02998  -0.0936   0.7839   1.0000
   3.000   0.5541   0.03988   0.03072  -0.0961   0.7691   1.0000
   3.250   0.5910   0.04052   0.03133  -0.0982   0.7539   1.0000
   3.500   0.6252   0.04120   0.03198  -0.0997   0.7390   1.0000
   3.750   0.6565   0.04195   0.03273  -0.1007   0.7243   1.0000
   4.000   0.6851   0.04282   0.03362  -0.1014   0.7098   1.0000
   4.250   0.7145   0.04360   0.03442  -0.1019   0.6954   1.0000
   4.500   0.7462   0.04415   0.03500  -0.1023   0.6805   1.0000
   4.750   0.7820   0.04424   0.03518  -0.1025   0.6650   1.0000
   5.000   0.8196   0.04409   0.03510  -0.1027   0.6497   1.0000
   5.250   0.8567   0.04394   0.03506  -0.1026   0.6348   1.0000
   5.500   0.8961   0.04334   0.03456  -0.1023   0.6195   1.0000
   5.750   0.9411   0.04199   0.03332  -0.1018   0.6031   1.0000
   6.000   0.9852   0.04063   0.03208  -0.1012   0.5862   1.0000
   6.250   1.0306   0.03918   0.03072  -0.1006   0.5689   1.0000
   6.500   1.0841   0.03688   0.02846  -0.1002   0.5498   1.0000
   6.750   1.1044   0.03723   0.02891  -0.0983   0.5264   1.0000
   7.000   1.1463   0.03597   0.02763  -0.0974   0.5037   1.0000
   7.250   1.1676   0.03654   0.02828  -0.0957   0.4800   1.0000
   7.500   1.2044   0.03584   0.02745  -0.0947   0.4545   1.0000
   7.750   1.2267   0.03602   0.02763  -0.0927   0.4264   1.0000
   8.000   1.2469   0.03640   0.02797  -0.0907   0.3980   1.0000
   8.250   1.2674   0.03695   0.02844  -0.0888   0.3705   1.0000
   8.500   1.2911   0.03757   0.02889  -0.0873   0.3446   1.0000
   8.750   1.3075   0.03887   0.03020  -0.0854   0.3207   1.0000
   9.000   1.3275   0.04005   0.03128  -0.0839   0.2984   1.0000
   9.250   1.3419   0.04182   0.03311  -0.0821   0.2788   1.0000
   9.500   1.3588   0.04370   0.03502  -0.0806   0.2613   1.0000
   9.750   1.3756   0.04553   0.03685  -0.0791   0.2448   1.0000
  10.000   1.3891   0.04761   0.03900  -0.0775   0.2305   1.0000
  10.250   1.4002   0.05010   0.04166  -0.0758   0.2186   1.0000
  10.500   1.4157   0.05244   0.04403  -0.0745   0.2075   1.0000
  10.750   1.4256   0.05509   0.04687  -0.0729   0.1985   1.0000
  11.000   1.4247   0.05852   0.05059  -0.0706   0.1923   1.0000
  11.250   1.4202   0.06183   0.05419  -0.0681   0.1865   1.0000
  11.500   1.4316   0.06485   0.05726  -0.0670   0.1798   1.0000
  11.750   1.4025   0.06930   0.06210  -0.0634   0.1786   1.0000
  12.000   1.3674   0.07437   0.06746  -0.0605   0.1784   1.0000
  12.250   1.3258   0.08084   0.07418  -0.0594   0.1790   1.0000
  12.500   1.2795   0.08922   0.08274  -0.0606   0.1802   1.0000
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