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FX 63-147 AIRFOIL (fx63147-il) Xfoil prediction polar at RE=1,000,000 Ncrit=0


Details Polar file
Airfoil: FX 63-147 AIRFOIL (fx63147-il)
Reynolds number: 1,000,000
Max Cl/Cd: 103.63 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63147-il-1000000.txt
Download as CSV file: xf-fx63147-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-147 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.3848   0.13860   0.13691  -0.0309   1.0001   0.0068
 -12.750  -0.3817   0.13546   0.13378  -0.0316   1.0001   0.0068
 -12.500  -0.3795   0.13202   0.13035  -0.0324   1.0001   0.0069
 -12.250  -0.3773   0.12869   0.12703  -0.0331   1.0001   0.0070
 -12.000  -0.3761   0.12512   0.12348  -0.0339   1.0001   0.0071
 -11.750  -0.3754   0.12153   0.11990  -0.0347   1.0001   0.0072
 -11.500  -0.3756   0.11779   0.11617  -0.0355   1.0001   0.0073
 -11.250  -0.3765   0.11397   0.11238  -0.0363   1.0001   0.0074
 -11.000  -0.3784   0.11005   0.10847  -0.0372   1.0001   0.0075
 -10.750  -0.3813   0.10599   0.10443  -0.0380   1.0001   0.0076
  -9.500  -0.3809   0.06605   0.06448  -0.0755   0.9931   0.0079
  -9.250  -0.3951   0.05776   0.05605  -0.0841   0.9882   0.0078
  -9.000  -0.4030   0.05081   0.04890  -0.0905   0.9846   0.0080
  -7.000  -0.2425   0.00948   0.00578  -0.1030   0.9005   0.0160
  -6.750  -0.2075   0.00736   0.00308  -0.1060   0.8822   0.0187
  -6.500  -0.1762   0.00630   0.00190  -0.1077   0.8594   0.0194
  -6.250  -0.1524   0.00557   0.00096  -0.1075   0.8349   0.0200
  -6.000  -0.1302   0.00494   0.00008  -0.1066   0.8130   0.0206
  -5.750  -0.1080   0.00448  -0.00059  -0.1057   0.7938   0.0215
  -5.500  -0.0884   0.01264   0.00702  -0.1068   0.8086   0.0111
  -5.250  -0.0694   0.01167   0.00598  -0.1052   0.7878   0.0106
  -5.000  -0.0495   0.01105   0.00524  -0.1038   0.7680   0.0101
  -4.750  -0.0289   0.01048   0.00454  -0.1026   0.7497   0.0096
  -4.500  -0.0062   0.01011   0.00405  -0.1018   0.7320   0.0092
  -4.250   0.0176   0.00987   0.00370  -0.1012   0.7147   0.0090
  -4.000   0.0423   0.00967   0.00341  -0.1007   0.6994   0.0088
  -3.750   0.0677   0.00950   0.00315  -0.1004   0.6859   0.0087
  -3.250   0.1206   0.00919   0.00269  -0.1002   0.6614   0.0086
  -3.000   0.1478   0.00909   0.00252  -0.1002   0.6501   0.0086
  -2.750   0.1749   0.00902   0.00238  -0.1002   0.6395   0.0087
  -2.500   0.2028   0.00896   0.00226  -0.1003   0.6291   0.0089
  -2.250   0.2308   0.00890   0.00217  -0.1005   0.6200   0.0097
  -2.000   0.2587   0.00887   0.00210  -0.1007   0.6107   0.0139
  -1.750   0.2876   0.00882   0.00203  -0.1011   0.6013   0.0198
  -1.500   0.3159   0.00876   0.00197  -0.1014   0.5926   0.0343
  -1.250   0.3451   0.00865   0.00191  -0.1019   0.5839   0.0646
  -1.000   0.3841   0.00774   0.00174  -0.1057   0.5760   0.3189
  -0.750   0.4404   0.00669   0.00162  -0.1135   0.5676   0.6162
  -0.500   0.4769   0.00659   0.00170  -0.1157   0.5608   0.6871
  -0.250   0.5086   0.00663   0.00182  -0.1166   0.5539   0.7273
   0.000   0.5379   0.00675   0.00195  -0.1169   0.5475   0.7519
   0.250   0.5680   0.00684   0.00202  -0.1175   0.5411   0.7625
   0.500   0.5948   0.00699   0.00215  -0.1173   0.5341   0.7712
   0.750   0.6248   0.00707   0.00220  -0.1179   0.5276   0.7766
   1.000   0.6516   0.00718   0.00230  -0.1177   0.5205   0.7812
   1.250   0.6790   0.00730   0.00242  -0.1176   0.5144   0.7866
   1.500   0.7079   0.00746   0.00251  -0.1179   0.5038   0.7925
   1.750   0.7327   0.00762   0.00263  -0.1173   0.4885   0.7963
   2.000   0.7583   0.00777   0.00275  -0.1169   0.4749   0.7998
   2.250   0.7854   0.00792   0.00286  -0.1168   0.4657   0.8037
   2.500   0.8140   0.00809   0.00298  -0.1172   0.4552   0.8074
   2.750   0.8403   0.00821   0.00308  -0.1169   0.4440   0.8099
   3.000   0.8656   0.00837   0.00320  -0.1165   0.4297   0.8118
   3.250   0.8904   0.00861   0.00334  -0.1160   0.4109   0.8139
   3.500   0.9161   0.00884   0.00350  -0.1158   0.3897   0.8160
   3.750   0.9420   0.00910   0.00366  -0.1157   0.3677   0.8181
   4.000   0.9685   0.00937   0.00382  -0.1157   0.3484   0.8202
   4.250   0.9955   0.00964   0.00400  -0.1158   0.3281   0.8223
   4.500   1.0203   0.00998   0.00422  -0.1156   0.3025   0.8240
   4.750   1.0407   0.01049   0.00454  -0.1144   0.2631   0.8257
   5.000   1.0597   0.01110   0.00493  -0.1130   0.2224   0.8275
   5.250   1.0759   0.01193   0.00548  -0.1112   0.1678   0.8296
   5.500   1.0920   0.01279   0.00607  -0.1094   0.1164   0.8317
   5.750   1.1109   0.01348   0.00658  -0.1081   0.0801   0.8337
   6.000   1.1320   0.01401   0.00699  -0.1072   0.0588   0.8356
   6.250   1.1563   0.01435   0.00731  -0.1069   0.0495   0.8373
   6.500   1.1761   0.01490   0.00777  -0.1058   0.0328   0.8390
   6.750   1.1954   0.01521   0.00809  -0.1044   0.0274   0.8405
   7.000   1.2118   0.01568   0.00854  -0.1026   0.0166   0.8421
   7.250   1.2310   0.01608   0.00894  -0.1013   0.0155   0.8436
   7.500   1.2510   0.01648   0.00936  -0.1001   0.0144   0.8454
   7.750   1.2712   0.01688   0.00978  -0.0991   0.0137   0.8473
   8.000   1.2913   0.01729   0.01023  -0.0980   0.0131   0.8493
   8.250   1.3112   0.01774   0.01071  -0.0970   0.0127   0.8510
   8.500   1.3310   0.01821   0.01123  -0.0961   0.0125   0.8526
   8.750   1.3499   0.01871   0.01177  -0.0950   0.0121   0.8540
   9.000   1.3658   0.01924   0.01237  -0.0934   0.0117   0.8555
   9.250   1.3801   0.01986   0.01306  -0.0915   0.0110   0.8570
   9.500   1.3924   0.02062   0.01389  -0.0895   0.0102   0.8586
   9.750   1.4033   0.02149   0.01483  -0.0873   0.0095   0.8602
  10.000   1.4222   0.02190   0.01527  -0.0864   0.0092   0.8617
  10.250   1.4391   0.02246   0.01586  -0.0853   0.0087   0.8633
  10.500   1.4553   0.02310   0.01653  -0.0842   0.0080   0.8649
  10.750   1.4703   0.02386   0.01733  -0.0831   0.0074   0.8664
  11.000   1.4833   0.02477   0.01827  -0.0818   0.0069   0.8678
  11.250   1.4974   0.02562   0.01917  -0.0806   0.0065   0.8693
  11.500   1.5102   0.02650   0.02012  -0.0794   0.0054   0.8707
  11.750   1.5177   0.02781   0.02142  -0.0777   0.0032   0.8722
  12.000   1.5240   0.02932   0.02300  -0.0761   0.0029   0.8736
  12.250   1.5297   0.03100   0.02475  -0.0747   0.0027   0.8750
  12.500   1.5353   0.03280   0.02664  -0.0736   0.0025   0.8765
  12.750   1.5405   0.03474   0.02866  -0.0726   0.0024   0.8779
  13.000   1.5449   0.03683   0.03084  -0.0718   0.0023   0.8794
  13.250   1.5479   0.03917   0.03328  -0.0711   0.0022   0.8809
  13.500   1.5500   0.04171   0.03591  -0.0706   0.0021   0.8821
  13.750   1.5512   0.04437   0.03868  -0.0702   0.0021   0.8832
  14.000   1.5515   0.04717   0.04158  -0.0698   0.0021   0.8844
  14.250   1.5499   0.05019   0.04471  -0.0695   0.0020   0.8855
  14.500   1.5474   0.05336   0.04800  -0.0693   0.0020   0.8867
  14.750   1.5438   0.05676   0.05151  -0.0692   0.0020   0.8879
  15.000   1.5399   0.06024   0.05510  -0.0692   0.0020   0.8891
  15.250   1.5348   0.06401   0.05899  -0.0694   0.0019   0.8901
  15.500   1.5295   0.06784   0.06293  -0.0697   0.0019   0.8911
  15.750   1.5233   0.07189   0.06708  -0.0702   0.0019   0.8921
  16.000   1.5166   0.07607   0.07137  -0.0708   0.0019   0.8930
  16.250   1.5089   0.08051   0.07593  -0.0716   0.0019   0.8938
  16.500   1.5013   0.08496   0.08048  -0.0724   0.0019   0.8946
  16.750   1.4926   0.08961   0.08524  -0.0734   0.0018   0.8954
  17.000   1.4842   0.09433   0.09007  -0.0746   0.0018   0.8961
  17.250   1.4755   0.09917   0.09502  -0.0759   0.0018   0.8967
  17.500   1.4666   0.10406   0.10001  -0.0773   0.0018   0.8975
  17.750   1.4578   0.10896   0.10503  -0.0788   0.0018   0.8985
  18.000   1.4482   0.11403   0.11021  -0.0804   0.0018   0.8993
  18.250   1.4385   0.11922   0.11550  -0.0822   0.0018   0.9000
  18.500   1.4300   0.12416   0.12055  -0.0841   0.0018   0.9008
  18.750   1.4204   0.12951   0.12601  -0.0863   0.0018   0.9015
  19.000   1.4109   0.13474   0.13135  -0.0885   0.0018   0.9022
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