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FX 78-K-140/20 (fx78k140-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 78-K-140/20 (fx78k140-il)
Reynolds number: 500,000
Max Cl/Cd: 125.09 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx78k140-il-500000.txt
Download as CSV file: xf-fx78k140-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 78-K-140/20                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.2377   0.04149   0.03778  -0.0873   0.7352   0.0209
  -6.500  -0.2540   0.03226   0.02789  -0.0805   0.7335   0.0149
  -6.250  -0.2528   0.02795   0.02313  -0.0765   0.7320   0.0141
  -6.000  -0.2459   0.02393   0.01855  -0.0727   0.7307   0.0138
  -5.750  -0.2276   0.02214   0.01644  -0.0709   0.7294   0.0148
  -5.500  -0.2067   0.02054   0.01454  -0.0695   0.7283   0.0154
  -5.250  -0.1836   0.01937   0.01315  -0.0686   0.7272   0.0158
  -5.000  -0.1620   0.01740   0.01090  -0.0675   0.7262   0.0174
  -4.750  -0.1383   0.01664   0.01005  -0.0669   0.7254   0.0191
  -4.500  -0.1147   0.01592   0.00920  -0.0661   0.7245   0.0199
  -4.250  -0.0909   0.01551   0.00872  -0.0654   0.7235   0.0225
  -4.000  -0.0666   0.01535   0.00853  -0.0649   0.7219   0.0244
  -3.750  -0.0471   0.01457   0.00772  -0.0635   0.7200   0.0288
  -3.500  -0.0228   0.01436   0.00750  -0.0629   0.7184   0.0339
  -3.250  -0.0001   0.01397   0.00708  -0.0620   0.7170   0.0411
  -3.000   0.0241   0.01371   0.00679  -0.0615   0.7156   0.0513
  -2.750   0.0486   0.01344   0.00655  -0.0609   0.7144   0.0666
  -2.500   0.0732   0.01320   0.00633  -0.0605   0.7133   0.0848
  -2.250   0.0968   0.01288   0.00615  -0.0599   0.7124   0.1232
  -2.000   0.1181   0.01241   0.00599  -0.0589   0.7114   0.2178
  -1.750   0.1350   0.01178   0.00587  -0.0571   0.7104   0.3786
  -1.500   0.1340   0.01088   0.00601  -0.0517   0.7078   0.6490
  -1.250   0.1481   0.01051   0.00628  -0.0486   0.7056   0.8314
  -1.000   0.1838   0.01052   0.00638  -0.0503   0.7042   0.8848
  -0.750   0.2217   0.01055   0.00637  -0.0524   0.7028   0.9104
  -0.500   0.2719   0.01065   0.00643  -0.0572   0.7018   0.9308
  -0.250   0.3189   0.01077   0.00648  -0.0613   0.7009   0.9428
   0.000   0.3590   0.01091   0.00655  -0.0639   0.7000   0.9532
   0.250   0.4252   0.01121   0.00678  -0.0717   0.6993   0.9597
   0.500   0.4757   0.01140   0.00690  -0.0763   0.6986   0.9683
   0.750   0.5178   0.01144   0.00689  -0.0796   0.6978   0.9708
   1.000   0.5552   0.01147   0.00686  -0.0819   0.6968   0.9737
   1.250   0.5847   0.01165   0.00708  -0.0829   0.6941   0.9778
   1.500   0.6179   0.01171   0.00715  -0.0845   0.6916   0.9808
   1.750   0.6537   0.01167   0.00711  -0.0866   0.6896   0.9826
   2.000   0.6885   0.01161   0.00704  -0.0885   0.6880   0.9849
   2.250   0.7219   0.01152   0.00694  -0.0900   0.6866   0.9875
   2.500   0.7544   0.01142   0.00682  -0.0913   0.6853   0.9899
   2.750   0.7900   0.01129   0.00667  -0.0932   0.6840   0.9914
   3.000   0.8243   0.01127   0.00668  -0.0950   0.6822   0.9935
   3.250   0.8565   0.01137   0.00687  -0.0967   0.6788   0.9961
   3.500   0.8905   0.01133   0.00687  -0.0985   0.6764   0.9981
   3.750   0.9257   0.01122   0.00679  -0.1005   0.6744   0.9999
   4.000   0.9512   0.01103   0.00662  -0.1002   0.6724   1.0000
   4.250   0.9759   0.01091   0.00651  -0.0999   0.6709   1.0000
   4.500   0.9992   0.01089   0.00653  -0.0993   0.6686   1.0000
   4.750   1.0183   0.01102   0.00677  -0.0982   0.6646   1.0000
   5.000   1.0411   0.01097   0.00677  -0.0975   0.6617   1.0000
   5.250   1.0684   0.01046   0.00627  -0.0972   0.6578   1.0000
   5.500   1.0895   0.01026   0.00615  -0.0961   0.6512   1.0000
   5.750   1.1153   0.00977   0.00564  -0.0955   0.6437   1.0000
   6.000   1.1350   0.00960   0.00556  -0.0942   0.6334   1.0000
   6.250   1.1538   0.00927   0.00523  -0.0923   0.6077   1.0000
   6.500   1.1683   0.00934   0.00518  -0.0899   0.5669   1.0000
   6.750   1.1609   0.01040   0.00578  -0.0839   0.4894   1.0000
   7.000   1.1441   0.01178   0.00687  -0.0767   0.4345   1.0000
   7.250   1.1143   0.01332   0.00823  -0.0676   0.3995   1.0000
   7.500   1.0954   0.01503   0.00977  -0.0612   0.3674   1.0000
   7.750   1.0703   0.01750   0.01190  -0.0548   0.3101   1.0000
   8.000   1.0450   0.02030   0.01425  -0.0489   0.2335   1.0000
   8.250   1.0119   0.02379   0.01705  -0.0426   0.1230   1.0000
   8.500   0.9874   0.02701   0.01964  -0.0376   0.0249   1.0000
   8.750   0.9990   0.02800   0.02062  -0.0364   0.0200   1.0000
   9.000   1.0061   0.02940   0.02209  -0.0345   0.0143   1.0000
   9.250   1.0146   0.03074   0.02351  -0.0329   0.0119   1.0000
   9.500   1.0186   0.03245   0.02529  -0.0310   0.0097   1.0000
   9.750   1.0258   0.03395   0.02687  -0.0295   0.0091   1.0000
  10.000   1.0354   0.03532   0.02830  -0.0283   0.0080   1.0000
  10.250   1.0389   0.03720   0.03029  -0.0265   0.0087   1.0000
  10.500   1.0468   0.03876   0.03190  -0.0252   0.0075   1.0000
  10.750   1.0519   0.04056   0.03379  -0.0237   0.0070   1.0000
  11.000   1.0566   0.04241   0.03574  -0.0220   0.0071   1.0000
  11.250   1.0628   0.04413   0.03753  -0.0205   0.0070   1.0000
  11.500   1.0716   0.04561   0.03909  -0.0191   0.0073   1.0000
  11.750   1.0813   0.04702   0.04056  -0.0176   0.0071   1.0000
  12.000   1.0959   0.04797   0.04161  -0.0153   0.0073   1.0000
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