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FX 63-110 AIRFOIL (fx63110-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 63-110 AIRFOIL (fx63110-il)
Reynolds number: 50,000
Max Cl/Cd: 40.04 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63110-il-50000.txt
Download as CSV file: xf-fx63110-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-110 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3399   0.12030   0.11317  -0.0327   1.0000   0.2203
  -9.250  -0.3103   0.11393   0.10676  -0.0307   1.0000   0.2309
  -9.000  -0.3371   0.11524   0.10827  -0.0315   1.0000   0.2361
  -8.750  -0.3163   0.11038   0.10340  -0.0297   1.0000   0.2502
  -8.500  -0.3029   0.10651   0.09957  -0.0284   1.0000   0.2607
  -8.250  -0.3174   0.10575   0.09897  -0.0277   1.0000   0.2687
  -8.000  -0.3156   0.10374   0.09703  -0.0260   1.0000   0.2816
  -7.750  -0.3018   0.09986   0.09318  -0.0244   1.0000   0.2918
  -7.500  -0.3391   0.10183   0.09542  -0.0218   1.0000   0.2986
  -7.250  -0.3180   0.09730   0.09087  -0.0201   1.0000   0.3126
  -7.000  -0.3115   0.09439   0.08803  -0.0178   1.0000   0.3239
  -6.750  -0.3506   0.09613   0.09000  -0.0133   1.0000   0.3303
  -6.500  -0.3413   0.09307   0.08697  -0.0108   1.0000   0.3452
  -6.250  -0.3365   0.09039   0.08435  -0.0082   1.0000   0.3580
  -6.000  -0.3797   0.09218   0.08636  -0.0027   1.0000   0.3629
  -5.750  -0.3721   0.08925   0.08347  -0.0001   1.0000   0.3778
  -4.500  -0.3201   0.04824   0.04125  -0.0680   1.0000   0.1698
  -4.250  -0.2750   0.04259   0.03499  -0.0762   1.0000   0.1650
  -4.000  -0.2244   0.03778   0.02927  -0.0841   1.0000   0.1612
  -3.750  -0.1887   0.03527   0.02630  -0.0872   1.0000   0.1634
  -3.500  -0.1546   0.03342   0.02396  -0.0896   1.0000   0.1696
  -3.250  -0.1215   0.03181   0.02187  -0.0915   1.0000   0.1739
  -3.000  -0.0962   0.03071   0.02077  -0.0918   1.0000   0.1829
  -2.750  -0.0701   0.02979   0.01973  -0.0921   1.0000   0.1944
  -2.500  -0.0444   0.02901   0.01891  -0.0922   1.0000   0.2085
  -2.250  -0.0179   0.02843   0.01840  -0.0927   1.0000   0.2347
  -2.000   0.0119   0.02787   0.01821  -0.0937   1.0000   0.2852
  -1.750   0.0404   0.02725   0.01907  -0.0932   1.0000   0.5137
  -1.500   0.0434   0.02824   0.02034  -0.0872   1.0000   0.6282
  -1.250   0.0481   0.02893   0.02108  -0.0821   1.0000   0.6878
  -1.000   0.0526   0.02938   0.02156  -0.0774   1.0000   0.7325
  -0.750   0.0582   0.02965   0.02183  -0.0731   1.0000   0.7743
  -0.500   0.0640   0.02979   0.02198  -0.0688   0.9977   0.8220
  -0.250   0.0740   0.02975   0.02200  -0.0648   0.9870   0.8860
   0.000   0.1005   0.02947   0.02174  -0.0659   0.9731   1.0000
   0.250   0.1682   0.03068   0.02254  -0.0767   0.9607   1.0000
   0.500   0.2266   0.03179   0.02333  -0.0850   0.9480   1.0000
   0.750   0.2777   0.03285   0.02414  -0.0916   0.9353   1.0000
   1.000   0.3249   0.03390   0.02498  -0.0971   0.9225   1.0000
   1.250   0.3693   0.03496   0.02586  -0.1019   0.9096   1.0000
   1.500   0.4131   0.03602   0.02677  -0.1062   0.8969   1.0000
   1.750   0.4603   0.03705   0.02768  -0.1107   0.8846   1.0000
   2.000   0.4954   0.03804   0.02859  -0.1133   0.8711   1.0000
   2.250   0.5271   0.03909   0.02958  -0.1152   0.8573   1.0000
   2.500   0.5593   0.04016   0.03060  -0.1171   0.8436   1.0000
   2.750   0.5926   0.04121   0.03164  -0.1190   0.8303   1.0000
   3.000   0.6287   0.04220   0.03261  -0.1211   0.8172   1.0000
   3.250   0.6734   0.04293   0.03335  -0.1240   0.8049   1.0000
   3.500   0.6994   0.04400   0.03446  -0.1246   0.7902   1.0000
   3.750   0.7268   0.04503   0.03553  -0.1252   0.7754   1.0000
   4.000   0.7566   0.04593   0.03648  -0.1258   0.7602   1.0000
   4.250   0.7885   0.04666   0.03729  -0.1265   0.7445   1.0000
   4.500   0.8217   0.04722   0.03794  -0.1270   0.7286   1.0000
   4.750   0.8549   0.04771   0.03852  -0.1274   0.7128   1.0000
   5.000   0.8892   0.04802   0.03897  -0.1276   0.6969   1.0000
   5.250   0.9242   0.04817   0.03925  -0.1277   0.6809   1.0000
   5.500   0.9614   0.04802   0.03928  -0.1277   0.6649   1.0000
   5.750   1.0029   0.04739   0.03883  -0.1276   0.6490   1.0000
   6.000   1.0501   0.04618   0.03783  -0.1277   0.6328   1.0000
   6.250   1.1002   0.04438   0.03627  -0.1274   0.6161   1.0000
   6.500   1.1654   0.04095   0.03307  -0.1275   0.5983   1.0000
   6.750   1.1954   0.03980   0.03209  -0.1251   0.5717   1.0000
   7.000   1.2454   0.03660   0.02899  -0.1235   0.5417   1.0000
   7.250   1.2835   0.03487   0.02730  -0.1217   0.5099   1.0000
   7.500   1.3190   0.03351   0.02582  -0.1199   0.4738   1.0000
   7.750   1.3376   0.03351   0.02573  -0.1168   0.4329   1.0000
   8.000   1.3533   0.03380   0.02577  -0.1136   0.3871   1.0000
   8.250   1.3621   0.03467   0.02637  -0.1098   0.3403   1.0000
   8.500   1.3692   0.03608   0.02743  -0.1063   0.2960   1.0000
   8.750   1.3796   0.03796   0.02889  -0.1035   0.2573   1.0000
   9.000   1.3968   0.04027   0.03080  -0.1019   0.2252   1.0000
   9.250   1.4125   0.04284   0.03342  -0.1002   0.2019   1.0000
   9.500   1.4366   0.04552   0.03604  -0.0996   0.1837   1.0000
   9.750   1.4558   0.04826   0.03888  -0.0986   0.1702   1.0000
  10.000   1.4755   0.05143   0.04225  -0.0976   0.1607   1.0000
  10.250   1.5041   0.05461   0.04529  -0.0980   0.1512   1.0000
  10.500   1.5020   0.05794   0.04930  -0.0947   0.1466   1.0000
  10.750   1.5114   0.06130   0.05295  -0.0930   0.1413   1.0000
  11.000   1.5293   0.06533   0.05704  -0.0925   0.1365   1.0000
  11.250   1.5145   0.06938   0.06165  -0.0889   0.1349   1.0000
  11.500   1.4955   0.07358   0.06628  -0.0854   0.1337   1.0000
  11.750   1.4713   0.07784   0.07090  -0.0819   0.1333   1.0000
  12.000   1.4429   0.08272   0.07609  -0.0794   0.1333   1.0000
  12.250   1.4116   0.08850   0.08214  -0.0782   0.1339   1.0000
  12.500   1.3786   0.09528   0.08916  -0.0786   0.1348   1.0000
  12.750   1.3457   0.10307   0.09713  -0.0805   0.1359   1.0000
  13.000   1.3166   0.11162   0.10581  -0.0835   0.1368   1.0000
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