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FX 63-145 AIRFOIL (fx63145-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 63-145 AIRFOIL (fx63145-il)
Reynolds number: 100,000
Max Cl/Cd: 56.8 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63145-il-100000.txt
Download as CSV file: xf-fx63145-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-145 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2904   0.09868   0.09458  -0.0415   1.0000   0.1087
  -8.500  -0.2770   0.09633   0.09228  -0.0393   1.0000   0.1130
  -8.250  -0.3052   0.09361   0.08975  -0.0418   1.0000   0.1172
  -8.000  -0.2874   0.09122   0.08742  -0.0385   1.0000   0.1216
  -7.750  -0.3083   0.08963   0.08603  -0.0374   1.0000   0.1261
  -7.500  -0.3402   0.08741   0.08406  -0.0409   0.9925   0.1282
  -7.250  -0.3017   0.08328   0.07989  -0.0446   0.9838   0.1404
  -7.000  -0.2707   0.07883   0.07544  -0.0503   0.9690   0.1536
  -5.750  -0.1148   0.03335   0.02669  -0.1149   0.8818   0.0598
  -5.500  -0.0701   0.02970   0.02234  -0.1177   0.8653   0.0516
  -5.250  -0.0302   0.02698   0.01919  -0.1194   0.8467   0.0477
  -5.000   0.0081   0.02545   0.01709  -0.1201   0.8274   0.0451
  -4.750   0.0404   0.02380   0.01529  -0.1203   0.8099   0.0444
  -4.500   0.0703   0.02255   0.01388  -0.1198   0.7929   0.0443
  -4.250   0.0985   0.02157   0.01280  -0.1192   0.7783   0.0448
  -4.000   0.1257   0.02066   0.01187  -0.1187   0.7655   0.0461
  -3.750   0.1528   0.01993   0.01112  -0.1188   0.7530   0.0512
  -3.500   0.1808   0.01930   0.01040  -0.1190   0.7414   0.0585
  -3.250   0.2121   0.01855   0.00944  -0.1198   0.7318   0.0713
  -3.000   0.2438   0.01627   0.00908  -0.1223   0.7216   0.4932
  -2.750   0.2684   0.01703   0.00985  -0.1203   0.7124   0.5788
  -2.500   0.2923   0.01769   0.01037  -0.1183   0.7031   0.6155
  -2.250   0.3121   0.01827   0.01092  -0.1154   0.6942   0.6403
  -2.000   0.3340   0.01869   0.01122  -0.1130   0.6857   0.6624
  -1.750   0.3564   0.01904   0.01147  -0.1112   0.6770   0.6839
  -1.500   0.3786   0.01920   0.01151  -0.1092   0.6691   0.6961
  -1.250   0.4028   0.01926   0.01147  -0.1082   0.6606   0.7064
  -1.000   0.4312   0.01929   0.01132  -0.1084   0.6525   0.7179
  -0.750   0.4543   0.01936   0.01132  -0.1070   0.6455   0.7262
  -0.500   0.4802   0.01943   0.01131  -0.1067   0.6382   0.7373
  -0.250   0.5070   0.01954   0.01126  -0.1062   0.6326   0.7507
   0.000   0.5255   0.01965   0.01143  -0.1039   0.6257   0.7625
   0.250   0.5470   0.01973   0.01147  -0.1022   0.6195   0.7759
   0.500   0.5705   0.01981   0.01145  -0.1009   0.6142   0.7899
   0.750   0.5919   0.01991   0.01159  -0.0996   0.6071   0.8037
   1.000   0.6137   0.01992   0.01155  -0.0981   0.6012   0.8158
   1.250   0.6350   0.01995   0.01154  -0.0966   0.5954   0.8270
   1.500   0.6569   0.02000   0.01162  -0.0955   0.5884   0.8393
   1.750   0.6806   0.02001   0.01157  -0.0945   0.5832   0.8516
   2.000   0.6999   0.02003   0.01163  -0.0927   0.5776   0.8628
   2.250   0.7214   0.02007   0.01170  -0.0916   0.5712   0.8745
   2.500   0.7468   0.02005   0.01162  -0.0911   0.5659   0.8866
   2.750   0.7665   0.02006   0.01169  -0.0896   0.5594   0.8977
   3.000   0.7892   0.02004   0.01168  -0.0888   0.5531   0.9095
   3.250   0.8153   0.01997   0.01152  -0.0883   0.5482   0.9227
   3.500   0.8351   0.02004   0.01172  -0.0872   0.5409   0.9378
   3.750   0.8617   0.01998   0.01170  -0.0871   0.5349   0.9547
   4.000   0.8972   0.02001   0.01173  -0.0890   0.5284   0.9765
   4.250   0.9314   0.02024   0.01203  -0.0911   0.5201   1.0000
   4.500   0.9675   0.02040   0.01216  -0.0934   0.5131   1.0000
   4.750   0.9994   0.02071   0.01257  -0.0951   0.5042   1.0000
   5.000   1.0361   0.02084   0.01263  -0.0973   0.4976   1.0000
   5.250   1.0674   0.02115   0.01306  -0.0988   0.4883   1.0000
   5.500   1.1038   0.02124   0.01307  -0.1009   0.4817   1.0000
   5.750   1.1329   0.02166   0.01366  -0.1020   0.4726   1.0000
   6.000   1.1671   0.02184   0.01379  -0.1035   0.4661   1.0000
   6.250   1.1935   0.02231   0.01444  -0.1041   0.4567   1.0000
   6.500   1.2244   0.02245   0.01457  -0.1049   0.4490   1.0000
   6.750   1.2488   0.02284   0.01516  -0.1049   0.4387   1.0000
   7.000   1.2754   0.02304   0.01541  -0.1050   0.4294   1.0000
   7.250   1.3021   0.02315   0.01553  -0.1050   0.4199   1.0000
   7.500   1.3257   0.02351   0.01598  -0.1046   0.4094   1.0000
   7.750   1.3508   0.02378   0.01628  -0.1044   0.3998   1.0000
   8.000   1.3718   0.02424   0.01687  -0.1036   0.3878   1.0000
   8.250   1.3913   0.02472   0.01750  -0.1026   0.3747   1.0000
   8.500   1.4116   0.02513   0.01798  -0.1016   0.3626   1.0000
   8.750   1.4316   0.02557   0.01841  -0.1006   0.3509   1.0000
   9.000   1.4504   0.02616   0.01895  -0.0994   0.3387   1.0000
   9.250   1.4639   0.02698   0.01989  -0.0976   0.3235   1.0000
   9.500   1.4743   0.02778   0.02078  -0.0954   0.3070   1.0000
   9.750   1.4831   0.02857   0.02148  -0.0930   0.2935   1.0000
  10.000   1.4903   0.02959   0.02236  -0.0904   0.2808   1.0000
  10.250   1.4929   0.03086   0.02372  -0.0875   0.2667   1.0000
  10.500   1.4946   0.03219   0.02519  -0.0849   0.2530   1.0000
  10.750   1.4973   0.03359   0.02660  -0.0826   0.2431   1.0000
  11.000   1.5010   0.03513   0.02813  -0.0806   0.2352   1.0000
  11.250   1.5080   0.03666   0.02959  -0.0791   0.2287   1.0000
  11.500   1.5140   0.03838   0.03143  -0.0777   0.2216   1.0000
  11.750   1.5195   0.04016   0.03327  -0.0765   0.2145   1.0000
  12.000   1.5204   0.04233   0.03568  -0.0753   0.2071   1.0000
  12.250   1.5206   0.04460   0.03807  -0.0744   0.2000   1.0000
  12.500   1.5190   0.04714   0.04073  -0.0738   0.1931   1.0000
  12.750   1.5162   0.04986   0.04343  -0.0734   0.1863   1.0000
  13.000   1.5132   0.05271   0.04618  -0.0730   0.1788   1.0000
  13.250   1.5084   0.05602   0.04960  -0.0729   0.1710   1.0000
  13.500   1.5036   0.05942   0.05308  -0.0731   0.1636   1.0000
  13.750   1.4964   0.06339   0.05735  -0.0737   0.1564   1.0000
  14.000   1.4911   0.06725   0.06143  -0.0745   0.1498   1.0000
  14.250   1.4855   0.07119   0.06547  -0.0753   0.1443   1.0000
  14.500   1.4813   0.07503   0.06939  -0.0762   0.1398   1.0000
  14.750   1.4780   0.07874   0.07307  -0.0770   0.1356   1.0000
  15.000   1.4768   0.08229   0.07668  -0.0777   0.1310   1.0000
  15.250   1.4767   0.08567   0.08013  -0.0783   0.1263   1.0000
  15.500   1.4732   0.08980   0.08444  -0.0794   0.1215   1.0000
  15.750   1.4649   0.09495   0.08988  -0.0813   0.1160   1.0000
  16.000   1.4540   0.10083   0.09614  -0.0836   0.1096   1.0000
  16.250   1.4432   0.10675   0.10229  -0.0862   0.1031   1.0000
  16.500   1.4315   0.11278   0.10832  -0.0892   0.0982   1.0000
  16.750   1.4199   0.11878   0.11424  -0.0921   0.0932   1.0000
  17.000   1.4107   0.12430   0.11968  -0.0946   0.0871   1.0000
  17.250   1.3995   0.13045   0.12595  -0.0977   0.0807   1.0000
  17.500   1.3841   0.13840   0.13449  -0.1019   0.0710   1.0000
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