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WORTMANN FX 76-120 (fx76120-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 76-120 (fx76120-il)
Reynolds number: 50,000
Max Cl/Cd: 26.69 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx76120-il-50000-n5.txt
Download as CSV file: xf-fx76120-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 76-120                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.7463   0.09139   0.08329  -0.0265   1.0000   0.0817
 -12.250  -0.8020   0.07751   0.06929  -0.0356   1.0000   0.0804
 -12.000  -0.8451   0.06853   0.06012  -0.0406   1.0000   0.0797
 -11.750  -0.8746   0.06273   0.05410  -0.0421   1.0000   0.0797
 -11.500  -0.8976   0.05838   0.04951  -0.0416   1.0000   0.0805
 -11.250  -0.9159   0.05484   0.04568  -0.0397   1.0000   0.0815
 -11.000  -0.9318   0.05172   0.04223  -0.0367   1.0000   0.0830
 -10.750  -0.9282   0.04950   0.03994  -0.0348   1.0000   0.0852
 -10.500  -0.9213   0.04767   0.03805  -0.0331   1.0000   0.0878
 -10.250  -0.9171   0.04562   0.03581  -0.0310   1.0000   0.0911
 -10.000  -0.9144   0.04325   0.03306  -0.0287   1.0000   0.0951
  -9.750  -0.9025   0.04164   0.03146  -0.0271   1.0000   0.0990
  -9.500  -0.8914   0.04007   0.02977  -0.0253   1.0000   0.1036
  -9.250  -0.8811   0.03822   0.02762  -0.0233   1.0000   0.1096
  -9.000  -0.8674   0.03702   0.02650  -0.0216   1.0000   0.1153
  -8.750  -0.8541   0.03544   0.02466  -0.0197   1.0000   0.1230
  -8.500  -0.8403   0.03436   0.02367  -0.0179   1.0000   0.1306
  -8.250  -0.8258   0.03311   0.02230  -0.0160   1.0000   0.1399
  -8.000  -0.8113   0.03196   0.02100  -0.0141   1.0000   0.1515
  -7.750  -0.7969   0.03102   0.02013  -0.0122   1.0000   0.1630
  -7.500  -0.7821   0.03009   0.01920  -0.0102   1.0000   0.1761
  -7.250  -0.7670   0.02923   0.01829  -0.0083   1.0000   0.1908
  -7.000  -0.7517   0.02843   0.01748  -0.0063   1.0000   0.2066
  -6.750  -0.7358   0.02769   0.01671  -0.0044   1.0000   0.2228
  -6.500  -0.7194   0.02699   0.01599  -0.0025   1.0000   0.2397
  -6.250  -0.7027   0.02633   0.01531  -0.0007   1.0000   0.2570
  -6.000  -0.6855   0.02570   0.01465   0.0011   1.0000   0.2746
  -5.750  -0.6679   0.02510   0.01402   0.0029   1.0000   0.2926
  -5.500  -0.6498   0.02452   0.01345   0.0046   1.0000   0.3106
  -5.250  -0.6313   0.02396   0.01293   0.0062   1.0000   0.3286
  -5.000  -0.6125   0.02342   0.01243   0.0079   1.0000   0.3473
  -4.750  -0.5934   0.02290   0.01195   0.0094   1.0000   0.3666
  -4.500  -0.5740   0.02240   0.01149   0.0110   1.0000   0.3873
  -4.250  -0.5546   0.02192   0.01102   0.0125   1.0000   0.4098
  -4.000  -0.5352   0.02146   0.01067   0.0141   1.0000   0.4328
  -3.750  -0.5160   0.02102   0.01031   0.0157   1.0000   0.4591
  -3.500  -0.4969   0.02061   0.01005   0.0173   1.0000   0.4867
  -3.250  -0.4786   0.02025   0.00981   0.0192   1.0000   0.5171
  -3.000  -0.4607   0.01994   0.00965   0.0212   1.0000   0.5511
  -2.750  -0.4425   0.01967   0.00954   0.0233   1.0000   0.5881
  -2.500  -0.4239   0.01947   0.00950   0.0253   1.0000   0.6282
  -2.250  -0.4037   0.01936   0.00957   0.0273   1.0000   0.6697
  -2.000  -0.3824   0.01934   0.00969   0.0290   1.0000   0.7132
  -1.750  -0.3578   0.01943   0.00990   0.0302   1.0000   0.7564
  -1.500  -0.3300   0.01960   0.01014   0.0308   1.0000   0.7982
  -1.250  -0.2972   0.01986   0.01043   0.0303   1.0000   0.8374
  -1.000  -0.2606   0.02017   0.01072   0.0289   1.0000   0.8738
  -0.750  -0.2167   0.02052   0.01105   0.0259   0.9997   0.9055
  -0.500  -0.1479   0.02094   0.01140   0.0179   0.9891   0.9289
  -0.250  -0.0733   0.02124   0.01165   0.0089   0.9778   0.9470
   0.000   0.0001   0.02133   0.01173   0.0000   0.9634   0.9634
   0.250   0.0732   0.02124   0.01166  -0.0089   0.9471   0.9780
   0.500   0.1482   0.02093   0.01139  -0.0180   0.9289   0.9892
   0.750   0.2169   0.02052   0.01104  -0.0259   0.9052   0.9997
   1.000   0.2606   0.02017   0.01072  -0.0289   0.8737   1.0000
   1.250   0.2971   0.01986   0.01043  -0.0303   0.8375   1.0000
   1.500   0.3300   0.01960   0.01014  -0.0308   0.7982   1.0000
   1.750   0.3578   0.01942   0.00990  -0.0302   0.7562   1.0000
   2.000   0.3824   0.01934   0.00969  -0.0290   0.7132   1.0000
   2.250   0.4037   0.01936   0.00956  -0.0272   0.6697   1.0000
   2.500   0.4239   0.01947   0.00949  -0.0253   0.6285   1.0000
   2.750   0.4425   0.01967   0.00954  -0.0233   0.5881   1.0000
   3.000   0.4607   0.01994   0.00965  -0.0212   0.5512   1.0000
   3.250   0.4786   0.02025   0.00981  -0.0192   0.5172   1.0000
   3.500   0.4968   0.02061   0.01005  -0.0173   0.4866   1.0000
   3.750   0.5160   0.02102   0.01030  -0.0157   0.4589   1.0000
   4.000   0.5352   0.02145   0.01067  -0.0141   0.4329   1.0000
   4.250   0.5546   0.02192   0.01102  -0.0125   0.4099   1.0000
   4.500   0.5741   0.02240   0.01149  -0.0110   0.3875   1.0000
   4.750   0.5934   0.02290   0.01195  -0.0094   0.3666   1.0000
   5.000   0.6125   0.02342   0.01243  -0.0079   0.3472   1.0000
   5.250   0.6313   0.02396   0.01293  -0.0062   0.3286   1.0000
   5.500   0.6498   0.02452   0.01345  -0.0046   0.3107   1.0000
   5.750   0.6679   0.02510   0.01402  -0.0029   0.2926   1.0000
   6.000   0.6855   0.02570   0.01465  -0.0011   0.2746   1.0000
   6.250   0.7028   0.02633   0.01531   0.0007   0.2571   1.0000
   6.500   0.7195   0.02699   0.01599   0.0025   0.2398   1.0000
   6.750   0.7357   0.02768   0.01671   0.0044   0.2227   1.0000
   7.000   0.7516   0.02842   0.01747   0.0063   0.2064   1.0000
   7.250   0.7670   0.02923   0.01831   0.0083   0.1908   1.0000
   7.500   0.7821   0.03009   0.01920   0.0102   0.1762   1.0000
   7.750   0.7970   0.03102   0.02012   0.0122   0.1630   1.0000
   8.000   0.8115   0.03196   0.02102   0.0141   0.1516   1.0000
   8.250   0.8260   0.03311   0.02231   0.0160   0.1400   1.0000
   8.500   0.8403   0.03435   0.02366   0.0179   0.1305   1.0000
   8.750   0.8541   0.03543   0.02465   0.0197   0.1229   1.0000
   9.000   0.8674   0.03700   0.02649   0.0216   0.1152   1.0000
   9.250   0.8810   0.03820   0.02759   0.0233   0.1094   1.0000
   9.500   0.8915   0.04005   0.02977   0.0252   0.1036   1.0000
   9.750   0.9028   0.04165   0.03147   0.0270   0.0990   1.0000
  10.000   0.9149   0.04327   0.03308   0.0286   0.0952   1.0000
  10.250   0.9175   0.04563   0.03583   0.0310   0.0912   1.0000
  10.500   0.9215   0.04769   0.03807   0.0330   0.0878   1.0000
  10.750   0.9286   0.04950   0.03993   0.0348   0.0851   1.0000
  11.000   0.9315   0.05175   0.04226   0.0367   0.0829   1.0000
  11.250   0.9163   0.05484   0.04568   0.0396   0.0815   1.0000
  11.500   0.8977   0.05842   0.04954   0.0415   0.0804   1.0000
  11.750   0.8753   0.06272   0.05408   0.0420   0.0797   1.0000
  12.000   0.8451   0.06860   0.06019   0.0405   0.0796   1.0000
  12.250   0.8020   0.07760   0.06938   0.0354   0.0803   1.0000
  12.500   0.7457   0.09170   0.08360   0.0261   0.0816   1.0000
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