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FX 60-100 AIRFOIL (fx60100-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 60-100 AIRFOIL (fx60100-il)
Reynolds number: 50,000
Max Cl/Cd: 42.58 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx60100-il-50000-n5.txt
Download as CSV file: xf-fx60100-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-100 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3783   0.11724   0.10988  -0.0343   1.0000   0.0574
 -10.000  -0.3702   0.11354   0.10621  -0.0342   1.0000   0.0535
  -9.750  -0.3807   0.10821   0.10099  -0.0388   1.0000   0.0475
  -9.500  -0.3718   0.10512   0.09793  -0.0379   1.0000   0.0462
  -9.250  -0.3686   0.10178   0.09464  -0.0383   1.0000   0.0451
  -9.000  -0.3677   0.09835   0.09130  -0.0389   1.0000   0.0441
  -8.750  -0.3684   0.09488   0.08791  -0.0396   1.0000   0.0431
  -8.500  -0.3714   0.09128   0.08442  -0.0404   1.0000   0.0422
  -8.250  -0.3763   0.08778   0.08104  -0.0410   1.0000   0.0413
  -8.000  -0.3848   0.08416   0.07755  -0.0415   1.0000   0.0403
  -7.750  -0.3978   0.08043   0.07399  -0.0418   1.0000   0.0394
  -7.250  -0.4296   0.06728   0.06092  -0.0533   1.0000   0.0365
  -6.750  -0.4331   0.05891   0.05234  -0.0577   1.0000   0.0360
  -6.500  -0.4284   0.05448   0.04771  -0.0604   1.0000   0.0358
  -6.250  -0.4180   0.04995   0.04285  -0.0634   1.0000   0.0356
  -6.000  -0.4019   0.04562   0.03811  -0.0662   1.0000   0.0355
  -5.750  -0.3812   0.04169   0.03368  -0.0686   1.0000   0.0355
  -5.500  -0.3576   0.03827   0.02973  -0.0704   1.0000   0.0358
  -5.250  -0.3325   0.03546   0.02638  -0.0716   1.0000   0.0364
  -5.000  -0.3088   0.03302   0.02370  -0.0723   1.0000   0.0383
  -4.750  -0.2852   0.03131   0.02180  -0.0725   1.0000   0.0412
  -4.500  -0.2608   0.02973   0.01995  -0.0724   1.0000   0.0439
  -4.250  -0.2365   0.02832   0.01823  -0.0718   1.0000   0.0462
  -4.000  -0.2120   0.02705   0.01680  -0.0715   1.0000   0.0488
  -3.750  -0.1863   0.02596   0.01562  -0.0718   1.0000   0.0545
  -3.500  -0.1597   0.02491   0.01447  -0.0723   1.0000   0.0663
  -3.250  -0.1187   0.02305   0.01284  -0.0762   0.9970   0.1130
  -3.000  -0.0775   0.02177   0.01303  -0.0803   0.9924   0.4051
  -2.750  -0.0435   0.02238   0.01357  -0.0812   0.9846   0.4812
  -2.500  -0.0111   0.02272   0.01377  -0.0817   0.9763   0.5206
  -2.250   0.0250   0.02294   0.01377  -0.0832   0.9688   0.5518
  -2.000   0.0587   0.02302   0.01365  -0.0843   0.9599   0.5751
  -1.750   0.0941   0.02308   0.01351  -0.0859   0.9516   0.5979
  -1.500   0.1295   0.02311   0.01341  -0.0874   0.9434   0.6178
  -1.250   0.1619   0.02313   0.01327  -0.0884   0.9343   0.6372
  -1.000   0.2004   0.02314   0.01314  -0.0905   0.9270   0.6561
  -0.750   0.2310   0.02312   0.01308  -0.0911   0.9167   0.6737
  -0.500   0.2641   0.02311   0.01299  -0.0921   0.9070   0.6930
  -0.250   0.3029   0.02305   0.01288  -0.0941   0.8990   0.7137
   0.000   0.3325   0.02300   0.01284  -0.0944   0.8878   0.7325
   0.250   0.3642   0.02294   0.01279  -0.0950   0.8776   0.7539
   0.500   0.4009   0.02275   0.01265  -0.0963   0.8698   0.7784
   0.750   0.4274   0.02262   0.01261  -0.0958   0.8577   0.8073
   1.000   0.4538   0.02239   0.01251  -0.0951   0.8456   0.8476
   1.250   0.4861   0.02207   0.01231  -0.0956   0.8330   1.0000
   1.500   0.5250   0.02215   0.01230  -0.0979   0.8220   1.0000
   1.750   0.5649   0.02216   0.01226  -0.1000   0.8122   1.0000
   2.000   0.5978   0.02228   0.01233  -0.1010   0.7990   1.0000
   2.250   0.6305   0.02234   0.01237  -0.1016   0.7853   1.0000
   2.500   0.6625   0.02240   0.01242  -0.1021   0.7714   1.0000
   2.750   0.6938   0.02246   0.01252  -0.1024   0.7572   1.0000
   3.000   0.7246   0.02253   0.01262  -0.1025   0.7429   1.0000
   3.250   0.7556   0.02253   0.01265  -0.1025   0.7277   1.0000
   3.500   0.7866   0.02250   0.01270  -0.1024   0.7118   1.0000
   3.750   0.8142   0.02262   0.01287  -0.1019   0.6934   1.0000
   4.000   0.8424   0.02269   0.01300  -0.1013   0.6746   1.0000
   4.250   0.8723   0.02263   0.01298  -0.1008   0.6548   1.0000
   4.500   0.8983   0.02275   0.01318  -0.0998   0.6310   1.0000
   4.750   0.9255   0.02282   0.01327  -0.0989   0.6067   1.0000
   5.000   0.9519   0.02295   0.01340  -0.0978   0.5805   1.0000
   5.250   0.9764   0.02319   0.01364  -0.0966   0.5516   1.0000
   5.500   0.9999   0.02355   0.01403  -0.0953   0.5216   1.0000
   5.750   1.0219   0.02400   0.01449  -0.0940   0.4895   1.0000
   6.000   1.0434   0.02452   0.01502  -0.0926   0.4575   1.0000
   6.250   1.0634   0.02512   0.01558  -0.0910   0.4226   1.0000
   6.500   1.0810   0.02586   0.01629  -0.0893   0.3828   1.0000
   6.750   1.0970   0.02676   0.01705  -0.0874   0.3412   1.0000
   7.000   1.1123   0.02780   0.01798  -0.0857   0.3017   1.0000
   7.250   1.1275   0.02900   0.01907  -0.0840   0.2673   1.0000
   7.500   1.1419   0.03034   0.02029  -0.0824   0.2369   1.0000
   7.750   1.1556   0.03181   0.02167  -0.0807   0.2091   1.0000
   8.000   1.1692   0.03334   0.02319  -0.0792   0.1851   1.0000
   8.250   1.1824   0.03496   0.02474  -0.0776   0.1666   1.0000
   8.500   1.1963   0.03659   0.02636  -0.0762   0.1500   1.0000
   8.750   1.2107   0.03824   0.02802  -0.0748   0.1373   1.0000
   9.000   1.2264   0.03995   0.02981  -0.0735   0.1263   1.0000
   9.250   1.2417   0.04168   0.03172  -0.0722   0.1161   1.0000
   9.500   1.2565   0.04346   0.03360  -0.0709   0.1079   1.0000
   9.750   1.2746   0.04535   0.03573  -0.0698   0.1016   1.0000
  10.000   1.2958   0.04751   0.03804  -0.0692   0.0965   1.0000
  10.250   1.3139   0.04988   0.04075  -0.0683   0.0917   1.0000
  10.500   1.3298   0.05199   0.04292  -0.0673   0.0872   1.0000
  10.750   1.3374   0.05463   0.04590  -0.0656   0.0831   1.0000
  11.000   1.3404   0.05739   0.04907  -0.0637   0.0795   1.0000
  11.250   1.3461   0.06030   0.05226  -0.0622   0.0769   1.0000
  11.500   1.3539   0.06322   0.05534  -0.0610   0.0746   1.0000
  11.750   1.3532   0.06688   0.05929  -0.0595   0.0730   1.0000
  12.000   1.3380   0.07115   0.06400  -0.0579   0.0719   1.0000
  12.250   1.3195   0.07588   0.06911  -0.0570   0.0710   1.0000
  12.500   1.2982   0.08123   0.07478  -0.0572   0.0703   1.0000
  12.750   1.2740   0.08742   0.08126  -0.0586   0.0700   1.0000
  13.000   1.2464   0.09476   0.08885  -0.0615   0.0702   1.0000
  13.250   1.2157   0.10349   0.09778  -0.0660   0.0709   1.0000
  13.500   1.1833   0.11381   0.10822  -0.0723   0.0718   1.0000
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