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FX 79-W-151 A (fx79w151a-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 79-W-151 A (fx79w151a-il)
Reynolds number: 50,000
Max Cl/Cd: 19.08 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx79w151a-il-50000-n5.txt
Download as CSV file: xf-fx79w151a-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 79-W-151 A                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3355   0.11256   0.10575  -0.0542   1.0000   0.0665
 -11.500  -0.3412   0.10782   0.10109  -0.0562   1.0000   0.0667
 -11.250  -0.3484   0.10311   0.09646  -0.0580   1.0000   0.0669
 -11.000  -0.3320   0.10340   0.09679  -0.0557   1.0000   0.0710
 -10.750  -0.3377   0.10006   0.09355  -0.0563   1.0000   0.0726
 -10.500  -0.3494   0.09643   0.09006  -0.0567   1.0000   0.0731
 -10.250  -0.3666   0.09308   0.08685  -0.0565   1.0000   0.0738
 -10.000  -0.3896   0.09011   0.08402  -0.0552   1.0000   0.0736
  -9.750  -0.4173   0.08728   0.08135  -0.0537   1.0000   0.0735
  -9.500  -0.4338   0.07755   0.07162  -0.0636   0.9874   0.0737
  -9.250  -0.4612   0.06859   0.06254  -0.0720   0.9720   0.0734
  -9.000  -0.4798   0.06183   0.05549  -0.0763   0.9580   0.0740
  -8.750  -0.4919   0.05625   0.04951  -0.0780   0.9451   0.0756
  -8.500  -0.5020   0.05134   0.04401  -0.0778   0.9326   0.0781
  -8.250  -0.4900   0.04916   0.04162  -0.0777   0.9228   0.0822
  -8.000  -0.4703   0.04684   0.03900  -0.0785   0.9155   0.0870
  -7.750  -0.4675   0.04402   0.03560  -0.0764   0.9042   0.0912
  -7.500  -0.4490   0.04265   0.03408  -0.0760   0.8959   0.0968
  -7.250  -0.4311   0.04085   0.03188  -0.0754   0.8876   0.1031
  -7.000  -0.4170   0.03917   0.02984  -0.0739   0.8784   0.1090
  -6.750  -0.3929   0.03807   0.02852  -0.0738   0.8715   0.1175
  -6.500  -0.3771   0.03684   0.02701  -0.0723   0.8621   0.1241
  -6.250  -0.3514   0.03579   0.02568  -0.0722   0.8558   0.1341
  -6.000  -0.3342   0.03501   0.02480  -0.0707   0.8466   0.1413
  -5.750  -0.3070   0.03396   0.02339  -0.0708   0.8405   0.1523
  -5.500  -0.2887   0.03343   0.02284  -0.0694   0.8316   0.1610
  -5.250  -0.2603   0.03260   0.02184  -0.0696   0.8256   0.1721
  -5.000  -0.2404   0.03208   0.02110  -0.0684   0.8170   0.1830
  -4.750  -0.2113   0.03138   0.02029  -0.0686   0.8109   0.1942
  -4.500  -0.1888   0.03093   0.01979  -0.0679   0.8032   0.2058
  -4.250  -0.1610   0.03038   0.01915  -0.0679   0.7966   0.2189
  -4.000  -0.1331   0.02989   0.01857  -0.0679   0.7902   0.2339
  -3.750  -0.1091   0.02953   0.01816  -0.0675   0.7826   0.2501
  -3.500  -0.0755   0.02889   0.01747  -0.0684   0.7781   0.2715
  -3.250  -0.0587   0.02873   0.01736  -0.0668   0.7686   0.2928
  -3.000  -0.0300   0.02812   0.01685  -0.0669   0.7637   0.3269
  -2.750  -0.0157   0.02795   0.01685  -0.0649   0.7549   0.3644
  -2.500   0.0071   0.02735   0.01657  -0.0638   0.7494   0.4325
  -2.250   0.0212   0.02706   0.01669  -0.0613   0.7416   0.5200
  -2.000   0.0490   0.02659   0.01677  -0.0602   0.7358   0.6561
  -1.750   0.1288   0.02630   0.01673  -0.0677   0.7330   0.8179
  -1.500   0.1928   0.02669   0.01693  -0.0737   0.7263   0.8936
  -1.250   0.2586   0.02686   0.01683  -0.0801   0.7210   0.9441
  -1.000   0.3370   0.02661   0.01626  -0.0893   0.7173   0.9837
  -0.750   0.3791   0.02684   0.01632  -0.0933   0.7089   1.0000
  -0.500   0.3973   0.02682   0.01612  -0.0919   0.7031   1.0000
  -0.250   0.4054   0.02730   0.01649  -0.0893   0.6942   1.0000
   0.000   0.4240   0.02737   0.01642  -0.0879   0.6884   1.0000
   0.250   0.4335   0.02788   0.01683  -0.0855   0.6802   1.0000
   0.500   0.4515   0.02805   0.01687  -0.0840   0.6740   1.0000
   0.750   0.4641   0.02851   0.01722  -0.0818   0.6667   1.0000
   1.000   0.4791   0.02887   0.01749  -0.0800   0.6598   1.0000
   1.250   0.5027   0.02891   0.01740  -0.0791   0.6552   1.0000
   1.500   0.5071   0.02979   0.01824  -0.0760   0.6459   1.0000
   1.750   0.5330   0.02978   0.01812  -0.0754   0.6417   1.0000
   2.000   0.5349   0.03084   0.01915  -0.0721   0.6324   1.0000
   2.250   0.5591   0.03094   0.01917  -0.0713   0.6277   1.0000
   2.500   0.5643   0.03192   0.02011  -0.0683   0.6194   1.0000
   2.750   0.5835   0.03228   0.02042  -0.0670   0.6139   1.0000
   3.000   0.6138   0.03217   0.02025  -0.0670   0.6106   1.0000
   3.250   0.6072   0.03374   0.02182  -0.0628   0.6001   1.0000
   3.500   0.6356   0.03374   0.02178  -0.0625   0.5965   1.0000
   3.750   0.6289   0.03542   0.02345  -0.0585   0.5867   1.0000
   4.000   0.6540   0.03559   0.02360  -0.0579   0.5824   1.0000
   4.500   0.6683   0.03781   0.02582  -0.0530   0.5685   1.0000
   4.750   0.6997   0.03772   0.02573  -0.0531   0.5656   1.0000
   5.000   0.6777   0.04032   0.02833  -0.0478   0.5543   1.0000
   5.250   0.7074   0.04036   0.02840  -0.0478   0.5512   1.0000
   5.750   0.7109   0.04353   0.03160  -0.0427   0.5366   1.0000
   6.250   0.7172   0.04715   0.03527  -0.0390   0.5220   1.0000
   6.500   0.7431   0.04738   0.03554  -0.0385   0.5192   1.0000
   6.750   0.7238   0.05119   0.03938  -0.0360   0.5075   1.0000
   7.000   0.7522   0.05122   0.03950  -0.0356   0.5051   1.0000
   7.250   0.7306   0.05548   0.04378  -0.0336   0.4935   1.0000
   7.500   0.7570   0.05572   0.04409  -0.0331   0.4906   1.0000
   8.000   0.7632   0.06022   0.04871  -0.0310   0.4764   1.0000
   8.500   0.7693   0.06494   0.05359  -0.0292   0.4626   1.0000
   8.750   0.7954   0.06526   0.05402  -0.0288   0.4600   1.0000
   9.000   0.7777   0.06954   0.05834  -0.0278   0.4492   1.0000
   9.250   0.8027   0.06993   0.05885  -0.0272   0.4458   1.0000
   9.500   0.7901   0.07381   0.06280  -0.0265   0.4358   1.0000
   9.750   0.8121   0.07445   0.06356  -0.0259   0.4316   1.0000
  10.000   0.8052   0.07789   0.06709  -0.0254   0.4226   1.0000
  10.250   0.8236   0.07885   0.06819  -0.0248   0.4174   1.0000
  10.750   0.8378   0.08293   0.07250  -0.0238   0.4028   1.0000
  11.250   0.8539   0.08679   0.07662  -0.0228   0.3878   1.0000
  11.750   0.8731   0.09021   0.08035  -0.0217   0.3723   1.0000
  12.000   0.8694   0.09342   0.08367  -0.0215   0.3620   1.0000
  12.250   0.8952   0.09312   0.08357  -0.0205   0.3564   1.0000
  12.500   0.8882   0.09672   0.08727  -0.0205   0.3449   1.0000
  12.750   0.9162   0.09590   0.08671  -0.0193   0.3393   1.0000
  14.250   0.9627   0.10359   0.09543  -0.0156   0.2692   1.0000
  14.750   0.9794   0.10430   0.09650  -0.0142   0.2307   1.0000
  15.000   0.9919   0.10403   0.09633  -0.0134   0.2026   1.0000
  15.250   1.0095   0.10303   0.09515  -0.0121   0.1631   1.0000
  15.500   1.0109   0.10509   0.09675  -0.0118   0.1282   1.0000
  15.750   1.0032   0.10926   0.10063  -0.0125   0.1052   1.0000
  16.000   0.9956   0.11358   0.10468  -0.0134   0.0895   1.0000
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