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FX 63-158 AIRFOIL (fx63158-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 63-158 AIRFOIL (fx63158-il)
Reynolds number: 50,000
Max Cl/Cd: 18.81 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63158-il-50000-n5.txt
Download as CSV file: xf-fx63158-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-158 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3089   0.11104   0.10437  -0.0513   1.0000   0.0599
 -10.000  -0.3269   0.10443   0.09789  -0.0554   1.0000   0.0535
  -9.750  -0.3213   0.10199   0.09553  -0.0541   1.0000   0.0524
  -9.500  -0.3237   0.09859   0.09224  -0.0541   1.0000   0.0509
  -9.000  -0.3635   0.08763   0.08150  -0.0587   1.0000   0.0461
  -8.750  -0.3771   0.08501   0.07901  -0.0577   1.0000   0.0456
  -8.500  -0.3987   0.08282   0.07695  -0.0558   1.0000   0.0451
  -8.250  -0.4076   0.07850   0.07263  -0.0595   0.9916   0.0442
  -8.000  -0.4091   0.07238   0.06632  -0.0674   0.9725   0.0428
  -7.750  -0.4154   0.06562   0.05897  -0.0748   0.9491   0.0404
  -7.500  -0.3994   0.06134   0.05448  -0.0782   0.9348   0.0398
  -7.250  -0.3810   0.05707   0.04989  -0.0816   0.9219   0.0390
  -7.000  -0.3604   0.05309   0.04552  -0.0845   0.9093   0.0383
  -6.750  -0.3391   0.04943   0.04141  -0.0866   0.8963   0.0376
  -6.500  -0.3111   0.04591   0.03737  -0.0889   0.8864   0.0372
  -6.250  -0.2799   0.04276   0.03372  -0.0910   0.8771   0.0369
  -6.000  -0.2497   0.04024   0.03077  -0.0922   0.8670   0.0369
  -5.750  -0.2139   0.03791   0.02803  -0.0937   0.8592   0.0372
  -5.500  -0.1832   0.03614   0.02597  -0.0939   0.8493   0.0378
  -5.250  -0.1459   0.03450   0.02407  -0.0945   0.8424   0.0387
  -5.000  -0.1156   0.03345   0.02278  -0.0935   0.8328   0.0400
  -4.750  -0.0820   0.03231   0.02156  -0.0932   0.8253   0.0427
  -4.500  -0.0565   0.03150   0.02060  -0.0923   0.8152   0.0460
  -4.250  -0.0274   0.03041   0.01947  -0.0927   0.8071   0.0497
  -4.000  -0.0053   0.02963   0.01858  -0.0923   0.7966   0.0539
  -3.750   0.0252   0.02858   0.01749  -0.0935   0.7891   0.0640
  -3.500   0.0464   0.02773   0.01671  -0.0934   0.7786   0.0828
  -3.250   0.0639   0.02483   0.01601  -0.0942   0.7714   0.3992
  -3.000   0.0709   0.02734   0.01893  -0.0856   0.7610   0.6364
  -2.750   0.0889   0.02911   0.02044  -0.0797   0.7542   0.6901
  -2.500   0.0992   0.03011   0.02128  -0.0739   0.7455   0.7184
  -2.250   0.1192   0.03058   0.02150  -0.0706   0.7389   0.7423
  -2.000   0.1399   0.03077   0.02146  -0.0681   0.7324   0.7601
  -1.750   0.1568   0.03088   0.02138  -0.0661   0.7246   0.7743
  -1.250   0.2013   0.03079   0.02088  -0.0646   0.7122   0.7920
  -1.000   0.2226   0.03075   0.02068  -0.0636   0.7061   0.7983
  -0.750   0.2523   0.03062   0.02034  -0.0644   0.7017   0.8059
  -0.500   0.2648   0.03081   0.02045  -0.0624   0.6948   0.8120
  -0.250   0.2862   0.03085   0.02036  -0.0619   0.6890   0.8173
   0.000   0.3178   0.03075   0.02007  -0.0631   0.6847   0.8220
   0.250   0.3299   0.03103   0.02030  -0.0613   0.6774   0.8276
   0.500   0.3509   0.03108   0.02025  -0.0605   0.6714   0.8333
   0.750   0.3836   0.03098   0.02000  -0.0616   0.6671   0.8388
   1.000   0.3929   0.03146   0.02047  -0.0597   0.6594   0.8439
   1.250   0.4150   0.03157   0.02052  -0.0592   0.6537   0.8477
   1.500   0.4482   0.03151   0.02034  -0.0604   0.6497   0.8513
   1.750   0.4555   0.03223   0.02109  -0.0585   0.6423   0.8556
   2.000   0.4793   0.03261   0.02142  -0.0589   0.6368   0.8590
   2.250   0.5097   0.03260   0.02136  -0.0596   0.6330   0.8622
   2.500   0.5163   0.03339   0.02219  -0.0573   0.6260   0.8669
   2.750   0.5345   0.03392   0.02272  -0.0568   0.6202   0.8716
   3.000   0.5674   0.03406   0.02283  -0.0582   0.6165   0.8754
   3.250   0.5781   0.03490   0.02372  -0.0568   0.6100   0.8787
   3.500   0.5918   0.03570   0.02458  -0.0558   0.6033   0.8817
   3.750   0.6250   0.03583   0.02469  -0.0572   0.5994   0.8840
   4.250   0.6514   0.03776   0.02673  -0.0557   0.5851   0.8904
   4.500   0.6884   0.03779   0.02680  -0.0574   0.5815   0.8932
   4.750   0.6762   0.03973   0.02885  -0.0539   0.5714   0.8973
   5.000   0.7046   0.04003   0.02919  -0.0545   0.5665   0.9001
   5.250   0.7470   0.03971   0.02890  -0.0565   0.5634   0.9024
   5.500   0.7317   0.04242   0.03173  -0.0537   0.5515   0.9064
   6.000   0.7561   0.04514   0.03466  -0.0530   0.5367   0.9137
   6.250   0.7863   0.04522   0.03483  -0.0535   0.5320   0.9176
   6.500   0.8312   0.04431   0.03399  -0.0549   0.5289   0.9211
   6.750   0.8101   0.04809   0.03791  -0.0530   0.5154   0.9266
   7.000   0.8587   0.04642   0.03635  -0.0539   0.5120   0.9303
   7.250   0.8434   0.04992   0.03997  -0.0526   0.4982   0.9365
   7.500   0.8947   0.04781   0.03798  -0.0534   0.4950   0.9414
   7.750   0.8779   0.05172   0.04203  -0.0526   0.4810   0.9496
   8.000   0.9295   0.04945   0.03991  -0.0532   0.4779   0.9571
   8.250   0.9100   0.05385   0.04445  -0.0529   0.4631   0.9778
   8.750   0.9487   0.05601   0.04692  -0.0543   0.4451   1.0000
   9.250   0.9897   0.05795   0.04916  -0.0556   0.4279   1.0000
   9.500   0.9857   0.06177   0.05312  -0.0565   0.4142   1.0000
  10.000   1.0224   0.06414   0.05583  -0.0577   0.3961   1.0000
  10.500   1.0266   0.07049   0.06247  -0.0596   0.3706   1.0000
  10.750   1.0596   0.06953   0.06172  -0.0596   0.3637   1.0000
  11.000   1.0631   0.07256   0.06491  -0.0605   0.3513   1.0000
  11.250   1.1067   0.07007   0.06264  -0.0602   0.3462   1.0000
  11.500   1.1013   0.07429   0.06701  -0.0613   0.3319   1.0000
  12.000   1.1081   0.08038   0.07344  -0.0630   0.3057   1.0000
  12.250   1.1367   0.07962   0.07286  -0.0628   0.2960   1.0000
  12.500   1.1621   0.07934   0.07278  -0.0627   0.2851   1.0000
  13.000   1.1692   0.08528   0.07901  -0.0643   0.2541   1.0000
  13.250   1.1892   0.08543   0.07921  -0.0641   0.2367   1.0000
  13.500   1.1995   0.08716   0.08092  -0.0644   0.2171   1.0000
  13.750   1.1975   0.09104   0.08486  -0.0656   0.1971   1.0000
  14.000   1.2063   0.09291   0.08652  -0.0659   0.1784   1.0000
  14.250   1.2070   0.09641   0.08994  -0.0669   0.1621   1.0000
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