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FX LIII-142 K 25 AIRFOIL (fxl142k-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX LIII-142 K 25 AIRFOIL (fxl142k-il)
Reynolds number: 50,000
Max Cl/Cd: 27.09 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fxl142k-il-50000.txt
Download as CSV file: xf-fxl142k-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX LIII-142 K 25 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.8541   0.07349   0.06625  -0.0219   1.0000   0.1752
 -10.750  -0.8874   0.06757   0.06025  -0.0224   1.0000   0.1739
 -10.500  -0.9160   0.06246   0.05496  -0.0217   1.0000   0.1731
 -10.250  -0.9358   0.05774   0.04994  -0.0206   1.0000   0.1731
 -10.000  -0.9481   0.05352   0.04533  -0.0191   1.0000   0.1741
  -9.750  -0.9560   0.04978   0.04110  -0.0173   1.0000   0.1764
  -9.500  -0.9295   0.04753   0.03904  -0.0172   1.0000   0.1838
  -9.250  -0.9242   0.04442   0.03553  -0.0158   1.0000   0.1884
  -9.000  -0.9132   0.04139   0.03215  -0.0146   1.0000   0.1930
  -8.750  -0.8908   0.03910   0.02981  -0.0140   1.0000   0.2006
  -8.500  -0.8734   0.03665   0.02714  -0.0131   1.0000   0.2095
  -8.250  -0.8550   0.03471   0.02510  -0.0120   1.0000   0.2232
  -8.000  -0.8332   0.03295   0.02351  -0.0111   1.0000   0.2412
  -7.750  -0.8124   0.03123   0.02197  -0.0099   1.0000   0.2631
  -7.500  -0.7928   0.02971   0.02068  -0.0084   1.0000   0.2903
  -7.250  -0.7749   0.02860   0.01983  -0.0065   1.0000   0.3241
  -7.000  -0.7583   0.02818   0.01973  -0.0040   1.0000   0.3654
  -6.750  -0.7394   0.02846   0.02030  -0.0012   1.0000   0.4101
  -6.500  -0.7095   0.03051   0.02266   0.0022   1.0000   0.4508
  -6.250  -0.6836   0.03223   0.02442   0.0057   1.0000   0.4887
  -6.000  -0.6505   0.03451   0.02673   0.0095   1.0000   0.5202
  -5.750  -0.6255   0.03553   0.02771   0.0127   1.0000   0.5478
  -5.500  -0.5942   0.03663   0.02874   0.0155   1.0000   0.5699
  -5.250  -0.5795   0.03641   0.02846   0.0184   1.0000   0.5925
  -5.000  -0.5498   0.03721   0.02922   0.0211   1.0000   0.6119
  -4.750  -0.5408   0.03692   0.02894   0.0244   1.0000   0.6316
  -4.500  -0.5484   0.03632   0.02838   0.0291   1.0000   0.6485
  -4.250  -0.5553   0.03594   0.02799   0.0338   1.0000   0.6633
  -4.000  -0.5602   0.03548   0.02750   0.0380   1.0000   0.6789
  -3.750  -0.5610   0.03504   0.02702   0.0418   1.0000   0.6954
  -3.500  -0.5519   0.03499   0.02692   0.0452   1.0000   0.7124
  -3.250  -0.5423   0.03483   0.02671   0.0483   1.0000   0.7296
  -3.000  -0.5331   0.03453   0.02636   0.0510   1.0000   0.7465
  -2.750  -0.5247   0.03405   0.02581   0.0534   1.0000   0.7617
  -2.500  -0.4978   0.03374   0.02540   0.0523   0.9952   0.7761
  -2.250  -0.4517   0.03363   0.02513   0.0477   0.9844   0.7905
  -2.000  -0.4071   0.03350   0.02487   0.0434   0.9741   0.8051
  -1.750  -0.3571   0.03349   0.02473   0.0385   0.9640   0.8193
  -1.500  -0.3106   0.03339   0.02454   0.0340   0.9540   0.8317
  -1.250  -0.2694   0.03319   0.02425   0.0301   0.9439   0.8432
  -1.000  -0.2345   0.03296   0.02395   0.0270   0.9339   0.8549
  -0.750  -0.1689   0.03311   0.02403   0.0193   0.9252   0.8654
  -0.500  -0.1132   0.03312   0.02400   0.0131   0.9155   0.8757
  -0.250  -0.0756   0.03309   0.02394   0.0097   0.9055   0.8866
   0.000  -0.0001   0.03313   0.02396   0.0000   0.8965   0.8965
   0.250   0.0755   0.03309   0.02394  -0.0097   0.8866   0.9056
   0.500   0.1138   0.03312   0.02400  -0.0131   0.8757   0.9155
   0.750   0.1688   0.03311   0.02403  -0.0193   0.8653   0.9252
   1.000   0.2348   0.03295   0.02394  -0.0271   0.8549   0.9339
   1.250   0.2696   0.03318   0.02425  -0.0301   0.8432   0.9439
   1.500   0.3107   0.03338   0.02453  -0.0340   0.8317   0.9539
   1.750   0.3571   0.03348   0.02472  -0.0385   0.8191   0.9640
   2.000   0.4072   0.03349   0.02486  -0.0434   0.8050   0.9742
   2.250   0.4521   0.03362   0.02511  -0.0478   0.7905   0.9845
   2.500   0.4981   0.03372   0.02537  -0.0523   0.7760   0.9952
   2.750   0.5245   0.03405   0.02582  -0.0534   0.7618   1.0000
   3.000   0.5330   0.03453   0.02635  -0.0510   0.7465   1.0000
   3.250   0.5418   0.03486   0.02674  -0.0483   0.7298   1.0000
   3.500   0.5521   0.03497   0.02690  -0.0452   0.7124   1.0000
   3.750   0.5607   0.03505   0.02704  -0.0418   0.6954   1.0000
   4.000   0.5600   0.03548   0.02750  -0.0380   0.6788   1.0000
   4.250   0.5552   0.03594   0.02799  -0.0338   0.6633   1.0000
   4.500   0.5478   0.03633   0.02839  -0.0290   0.6483   1.0000
   4.750   0.5407   0.03691   0.02893  -0.0244   0.6315   1.0000
   5.000   0.5499   0.03720   0.02921  -0.0211   0.6119   1.0000
   5.250   0.5797   0.03639   0.02844  -0.0184   0.5925   1.0000
   5.500   0.5943   0.03661   0.02873  -0.0155   0.5698   1.0000
   5.750   0.6255   0.03554   0.02771  -0.0127   0.5478   1.0000
   6.000   0.6503   0.03454   0.02677  -0.0095   0.5202   1.0000
   6.250   0.6836   0.03224   0.02443  -0.0057   0.4887   1.0000
   6.500   0.7095   0.03050   0.02265  -0.0022   0.4507   1.0000
   6.750   0.7395   0.02845   0.02030   0.0012   0.4101   1.0000
   7.000   0.7583   0.02818   0.01973   0.0040   0.3654   1.0000
   7.250   0.7750   0.02861   0.01984   0.0065   0.3243   1.0000
   7.500   0.7929   0.02971   0.02068   0.0084   0.2903   1.0000
   7.750   0.8123   0.03123   0.02197   0.0099   0.2628   1.0000
   8.000   0.8333   0.03295   0.02352   0.0111   0.2411   1.0000
   8.250   0.8550   0.03471   0.02511   0.0120   0.2232   1.0000
   8.500   0.8735   0.03666   0.02714   0.0131   0.2095   1.0000
   8.750   0.8908   0.03910   0.02981   0.0140   0.2005   1.0000
   9.000   0.9134   0.04139   0.03214   0.0146   0.1929   1.0000
   9.250   0.9242   0.04443   0.03554   0.0158   0.1883   1.0000
   9.500   0.9297   0.04751   0.03901   0.0172   0.1836   1.0000
   9.750   0.9570   0.04981   0.04108   0.0173   0.1762   1.0000
  10.000   0.9481   0.05352   0.04534   0.0191   0.1741   1.0000
  10.250   0.9354   0.05777   0.04998   0.0205   0.1730   1.0000
  10.500   0.9156   0.06250   0.05500   0.0216   0.1730   1.0000
  10.750   0.8864   0.06762   0.06030   0.0224   0.1738   1.0000
  11.000   0.8534   0.07357   0.06633   0.0218   0.1751   1.0000
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