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FX 63-145 AIRFOIL (fx63145-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 63-145 AIRFOIL (fx63145-il)
Reynolds number: 50,000
Max Cl/Cd: 33.7 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63145-il-50000-n5.txt
Download as CSV file: xf-fx63145-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2935   0.09785   0.09149  -0.0469   1.0000   0.0379
  -9.000  -0.2924   0.09475   0.08850  -0.0470   1.0000   0.0372
  -8.750  -0.2951   0.09122   0.08509  -0.0477   1.0000   0.0365
  -8.500  -0.3006   0.08743   0.08143  -0.0485   1.0000   0.0357
  -8.250  -0.3100   0.08329   0.07742  -0.0496   1.0000   0.0347
  -8.000  -0.3278   0.07886   0.07315  -0.0507   1.0000   0.0338
  -7.750  -0.3568   0.07561   0.07008  -0.0503   1.0000   0.0332
  -7.500  -0.3713   0.06857   0.06288  -0.0602   0.9856   0.0319
  -7.250  -0.3546   0.06301   0.05713  -0.0679   0.9642   0.0315
  -7.000  -0.3359   0.05770   0.05151  -0.0747   0.9442   0.0310
  -6.750  -0.3130   0.05274   0.04616  -0.0807   0.9266   0.0306
  -6.500  -0.2859   0.04824   0.04119  -0.0856   0.9109   0.0304
  -6.250  -0.2545   0.04431   0.03673  -0.0899   0.8969   0.0305
  -6.000  -0.2174   0.04076   0.03255  -0.0940   0.8851   0.0313
  -5.750  -0.1796   0.03784   0.02910  -0.0972   0.8729   0.0326
  -5.500  -0.1454   0.03566   0.02664  -0.0992   0.8592   0.0341
  -5.250  -0.1092   0.03365   0.02428  -0.1007   0.8466   0.0354
  -5.000  -0.0718   0.03187   0.02219  -0.1016   0.8354   0.0364
  -4.750  -0.0397   0.03058   0.02062  -0.1014   0.8220   0.0376
  -4.500  -0.0103   0.02948   0.01933  -0.1010   0.8088   0.0390
  -4.250   0.0191   0.02835   0.01804  -0.1013   0.7971   0.0414
  -4.000   0.0499   0.02735   0.01680  -0.1021   0.7868   0.0445
  -3.750   0.0779   0.02638   0.01573  -0.1030   0.7757   0.0490
  -3.500   0.1109   0.02538   0.01456  -0.1045   0.7669   0.0616
  -3.250   0.1402   0.02246   0.01356  -0.1084   0.7568   0.3550
  -3.000   0.1578   0.02347   0.01517  -0.1039   0.7481   0.5635
  -2.750   0.1757   0.02441   0.01596  -0.1000   0.7386   0.6115
  -2.500   0.2025   0.02465   0.01590  -0.0992   0.7299   0.6341
  -2.250   0.2252   0.02493   0.01597  -0.0973   0.7212   0.6529
  -2.000   0.2486   0.02514   0.01598  -0.0958   0.7132   0.6709
  -1.750   0.2721   0.02531   0.01596  -0.0947   0.7050   0.6876
  -1.500   0.2984   0.02540   0.01584  -0.0941   0.6981   0.7027
  -1.250   0.3217   0.02552   0.01581  -0.0933   0.6897   0.7155
  -1.000   0.3486   0.02552   0.01560  -0.0926   0.6832   0.7273
  -0.750   0.3713   0.02565   0.01562  -0.0919   0.6739   0.7388
  -0.500   0.4021   0.02561   0.01535  -0.0924   0.6669   0.7505
  -0.250   0.4218   0.02576   0.01545  -0.0909   0.6579   0.7597
   0.000   0.4509   0.02575   0.01525  -0.0910   0.6505   0.7705
   0.250   0.4719   0.02591   0.01536  -0.0900   0.6414   0.7805
   0.500   0.4989   0.02588   0.01519  -0.0896   0.6338   0.7907
   0.750   0.5224   0.02607   0.01532  -0.0893   0.6248   0.8020
   1.000   0.5467   0.02604   0.01519  -0.0883   0.6174   0.8116
   1.250   0.5696   0.02622   0.01534  -0.0877   0.6093   0.8221
   1.500   0.5939   0.02629   0.01535  -0.0871   0.6019   0.8326
   1.750   0.6176   0.02640   0.01541  -0.0864   0.5949   0.8431
   2.000   0.6400   0.02662   0.01564  -0.0858   0.5868   0.8546
   2.250   0.6659   0.02657   0.01551  -0.0852   0.5804   0.8655
   2.500   0.6840   0.02685   0.01587  -0.0840   0.5713   0.8774
   2.750   0.7115   0.02673   0.01569  -0.0836   0.5647   0.8912
   3.000   0.7289   0.02699   0.01604  -0.0823   0.5554   0.9080
   3.250   0.7576   0.02683   0.01583  -0.0822   0.5487   0.9266
   3.500   0.7821   0.02715   0.01624  -0.0825   0.5394   0.9523
   3.750   0.8192   0.02716   0.01621  -0.0845   0.5323   1.0000
   4.000   0.8454   0.02781   0.01696  -0.0855   0.5232   1.0000
   4.250   0.8788   0.02807   0.01717  -0.0871   0.5160   1.0000
   4.500   0.9040   0.02877   0.01794  -0.0879   0.5071   1.0000
   4.750   0.9357   0.02906   0.01822  -0.0891   0.5001   1.0000
   5.000   0.9607   0.02976   0.01904  -0.0897   0.4921   1.0000
   5.250   0.9899   0.03016   0.01947  -0.0905   0.4853   1.0000
   5.500   1.0164   0.03071   0.02006  -0.0910   0.4783   1.0000
   5.750   1.0403   0.03135   0.02083  -0.0912   0.4704   1.0000
   6.000   1.0687   0.03171   0.02121  -0.0916   0.4641   1.0000
   6.250   1.0843   0.03280   0.02248  -0.0909   0.4547   1.0000
   6.500   1.1087   0.03331   0.02308  -0.0909   0.4476   1.0000
   6.750   1.1229   0.03441   0.02435  -0.0899   0.4383   1.0000
   7.000   1.1440   0.03503   0.02506  -0.0895   0.4307   1.0000
   7.250   1.1625   0.03571   0.02586  -0.0887   0.4221   1.0000
   7.500   1.1819   0.03630   0.02656  -0.0879   0.4138   1.0000
   7.750   1.2008   0.03691   0.02727  -0.0871   0.4052   1.0000
   8.000   1.2100   0.03813   0.02863  -0.0855   0.3960   1.0000
   8.250   1.2244   0.03891   0.02951  -0.0842   0.3871   1.0000
   8.500   1.2183   0.04113   0.03191  -0.0817   0.3761   1.0000
   8.750   1.2280   0.04231   0.03320  -0.0804   0.3669   1.0000
   9.000   1.2450   0.04292   0.03389  -0.0794   0.3583   1.0000
   9.250   1.2528   0.04436   0.03543  -0.0782   0.3488   1.0000
   9.500   1.2809   0.04402   0.03508  -0.0775   0.3402   1.0000
   9.750   1.2652   0.04772   0.03899  -0.0760   0.3284   1.0000
  10.000   1.2547   0.05137   0.04280  -0.0754   0.3170   1.0000
  10.250   1.2589   0.05353   0.04508  -0.0749   0.3069   1.0000
  10.500   1.2765   0.05410   0.04568  -0.0741   0.2977   1.0000
  10.750   1.2831   0.05608   0.04773  -0.0736   0.2882   1.0000
  11.000   1.3005   0.05676   0.04839  -0.0728   0.2796   1.0000
  11.250   1.2940   0.06056   0.05235  -0.0729   0.2696   1.0000
  11.500   1.2788   0.06576   0.05775  -0.0737   0.2596   1.0000
  11.750   1.2802   0.06875   0.06086  -0.0738   0.2514   1.0000
  12.000   1.2832   0.07159   0.06381  -0.0740   0.2440   1.0000
  12.250   1.2982   0.07269   0.06495  -0.0734   0.2383   1.0000
  12.500   1.3018   0.07558   0.06797  -0.0736   0.2321   1.0000
  12.750   1.3284   0.07506   0.06747  -0.0724   0.2274   1.0000
  13.000   1.3052   0.08216   0.07482  -0.0744   0.2206   1.0000
  13.250   1.3101   0.08501   0.07780  -0.0746   0.2153   1.0000
  13.500   1.2704   0.09545   0.08846  -0.0784   0.2085   1.0000
  13.750   1.2539   0.10235   0.09551  -0.0809   0.2027   1.0000
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