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FX 60-100 (126) AIRFOIL (fx601001-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 60-100 (126) AIRFOIL (fx601001-il)
Reynolds number: 50,000
Max Cl/Cd: 38.27 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx601001-il-50000.txt
Download as CSV file: xf-fx601001-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-100 (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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3610   0.10517   0.09839  -0.0227   1.0000   0.2671
  -8.250  -0.3468   0.10088   0.09411  -0.0219   1.0000   0.2749
  -8.000  -0.3580   0.09956   0.09294  -0.0217   1.0000   0.2841
  -7.750  -0.3588   0.09754   0.09098  -0.0206   1.0000   0.2967
  -7.500  -0.3500   0.09429   0.08778  -0.0193   1.0000   0.3103
  -7.250  -0.3415   0.09106   0.08459  -0.0179   1.0000   0.3229
  -7.000  -0.3372   0.08814   0.08175  -0.0166   1.0000   0.3331
  -6.750  -0.3480   0.08663   0.08039  -0.0147   1.0000   0.3426
  -6.500  -0.3437   0.08375   0.07757  -0.0131   1.0000   0.3490
  -6.250  -0.4260   0.06819   0.06230  -0.0452   1.0000   0.1667
  -6.000  -0.4191   0.05818   0.05206  -0.0546   1.0000   0.1355
  -5.750  -0.4012   0.04929   0.04256  -0.0643   1.0000   0.1215
  -5.500  -0.3783   0.04386   0.03666  -0.0686   1.0000   0.1190
  -5.250  -0.3497   0.03903   0.03116  -0.0727   1.0000   0.1202
  -5.000  -0.3183   0.03494   0.02636  -0.0756   1.0000   0.1218
  -4.750  -0.2867   0.03160   0.02232  -0.0773   1.0000   0.1254
  -4.500  -0.2592   0.02942   0.01980  -0.0778   1.0000   0.1388
  -4.250  -0.2335   0.02724   0.01763  -0.0777   1.0000   0.1557
  -4.000  -0.2076   0.02555   0.01600  -0.0776   1.0000   0.1859
  -3.750  -0.1810   0.02404   0.01457  -0.0776   1.0000   0.2262
  -3.500  -0.1533   0.02241   0.01331  -0.0778   1.0000   0.2852
  -3.250  -0.1357   0.02254   0.01464  -0.0744   1.0000   0.4299
  -3.000  -0.1277   0.02390   0.01609  -0.0685   1.0000   0.5308
  -2.750  -0.1188   0.02448   0.01665  -0.0636   1.0000   0.5834
  -2.500  -0.1108   0.02477   0.01694  -0.0588   1.0000   0.6195
  -2.250  -0.1020   0.02497   0.01710  -0.0545   1.0000   0.6581
  -2.000  -0.0969   0.02510   0.01720  -0.0494   1.0000   0.6996
  -1.750  -0.0935   0.02494   0.01707  -0.0441   1.0000   0.7362
  -1.500  -0.0820   0.02468   0.01671  -0.0413   1.0000   0.7696
  -1.250  -0.0679   0.02437   0.01628  -0.0395   1.0000   0.7946
  -1.000  -0.0507   0.02414   0.01593  -0.0386   1.0000   0.8171
  -0.750  -0.0330   0.02400   0.01568  -0.0380   1.0000   0.8380
  -0.500  -0.0146   0.02394   0.01550  -0.0377   1.0000   0.8584
  -0.250   0.0027   0.02392   0.01542  -0.0372   1.0000   0.8797
   0.000   0.0207   0.02394   0.01543  -0.0369   1.0000   0.9062
   0.250   0.0433   0.02396   0.01548  -0.0383   1.0000   0.9530
   0.500   0.0734   0.02443   0.01582  -0.0421   0.9974   1.0000
   0.750   0.1322   0.02574   0.01691  -0.0507   0.9852   1.0000
   1.000   0.1872   0.02694   0.01793  -0.0584   0.9725   1.0000
   1.250   0.2399   0.02808   0.01892  -0.0653   0.9589   1.0000
   1.500   0.2910   0.02915   0.01988  -0.0718   0.9447   1.0000
   1.750   0.3411   0.03017   0.02081  -0.0777   0.9299   1.0000
   2.000   0.3899   0.03112   0.02170  -0.0831   0.9148   1.0000
   2.250   0.4373   0.03200   0.02255  -0.0881   0.8997   1.0000
   2.500   0.4849   0.03281   0.02336  -0.0927   0.8842   1.0000
   2.750   0.5293   0.03354   0.02409  -0.0965   0.8680   1.0000
   3.000   0.5659   0.03426   0.02483  -0.0990   0.8503   1.0000
   3.250   0.6069   0.03485   0.02550  -0.1016   0.8322   1.0000
   3.500   0.6545   0.03515   0.02588  -0.1047   0.8141   1.0000
   3.750   0.7026   0.03517   0.02606  -0.1072   0.7948   1.0000
   4.000   0.7445   0.03510   0.02612  -0.1084   0.7729   1.0000
   4.250   0.8057   0.03387   0.02510  -0.1108   0.7540   1.0000
   4.500   0.8387   0.03371   0.02513  -0.1102   0.7305   1.0000
   4.750   0.8910   0.03232   0.02394  -0.1107   0.7109   1.0000
   5.000   0.9232   0.03198   0.02378  -0.1095   0.6859   1.0000
   5.250   0.9606   0.03125   0.02325  -0.1084   0.6610   1.0000
   5.500   0.9984   0.03043   0.02257  -0.1071   0.6347   1.0000
   5.750   1.0309   0.03003   0.02228  -0.1055   0.6052   1.0000
   6.250   1.0888   0.03001   0.02242  -0.1018   0.5415   1.0000
   6.500   1.1171   0.03003   0.02242  -0.0999   0.5088   1.0000
   6.750   1.1401   0.03044   0.02287  -0.0979   0.4755   1.0000
   7.000   1.1624   0.03088   0.02337  -0.0958   0.4427   1.0000
   7.250   1.1861   0.03103   0.02346  -0.0937   0.4082   1.0000
   7.500   1.2031   0.03144   0.02377  -0.0909   0.3675   1.0000
   7.750   1.2130   0.03190   0.02395  -0.0875   0.3178   1.0000
   8.000   1.2152   0.03294   0.02467  -0.0835   0.2628   1.0000
   8.250   1.2106   0.03517   0.02654  -0.0791   0.1988   1.0000
   8.500   1.2116   0.03824   0.02907  -0.0755   0.1474   1.0000
   8.750   1.2285   0.04128   0.03193  -0.0736   0.1201   1.0000
   9.000   1.2489   0.04411   0.03479  -0.0723   0.1046   1.0000
   9.250   1.2710   0.04728   0.03808  -0.0714   0.0946   1.0000
   9.500   1.2938   0.05092   0.04199  -0.0705   0.0890   1.0000
   9.750   1.3155   0.05546   0.04665  -0.0699   0.0854   1.0000
  10.000   1.3187   0.05952   0.05136  -0.0675   0.0837   1.0000
  10.250   1.3164   0.06375   0.05612  -0.0651   0.0823   1.0000
  10.500   1.3087   0.06805   0.06088  -0.0627   0.0813   1.0000
  10.750   1.2952   0.07239   0.06560  -0.0603   0.0810   1.0000
  11.000   1.2758   0.07669   0.07020  -0.0579   0.0813   1.0000
  11.250   1.2534   0.08142   0.07520  -0.0565   0.0818   1.0000
  11.500   1.2296   0.08677   0.08078  -0.0564   0.0826   1.0000
  11.750   1.2057   0.09281   0.08700  -0.0577   0.0835   1.0000
  12.000   1.1833   0.09948   0.09381  -0.0600   0.0844   1.0000
  12.250   1.1643   0.10660   0.10103  -0.0629   0.0853   1.0000
  12.500   1.0764   0.12816   0.12270  -0.0806   0.0971   1.0000
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