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FX 79-L-120 (fx79l120-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 79-L-120 (fx79l120-il)
Reynolds number: 50,000
Max Cl/Cd: 27.94 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx79l120-il-50000-n5.txt
Download as CSV file: xf-fx79l120-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 79-L-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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.7428   0.09777   0.09006  -0.0139   1.0000   0.0655
 -12.000  -0.7660   0.08931   0.08157  -0.0191   1.0000   0.0649
 -11.750  -0.7946   0.08129   0.07346  -0.0242   1.0000   0.0644
 -11.500  -0.8234   0.07450   0.06654  -0.0280   1.0000   0.0641
 -11.250  -0.8486   0.06905   0.06091  -0.0300   1.0000   0.0639
 -11.000  -0.8713   0.06467   0.05631  -0.0303   1.0000   0.0642
 -10.750  -0.8899   0.06103   0.05242  -0.0289   1.0000   0.0646
 -10.500  -0.9052   0.05743   0.04844  -0.0271   1.0000   0.0656
 -10.250  -0.9111   0.05404   0.04469  -0.0255   1.0000   0.0666
 -10.000  -0.9000   0.05149   0.04211  -0.0247   1.0000   0.0686
  -9.750  -0.8908   0.04894   0.03936  -0.0236   1.0000   0.0704
  -9.500  -0.8809   0.04655   0.03673  -0.0224   1.0000   0.0733
  -9.250  -0.8710   0.04405   0.03382  -0.0210   1.0000   0.0767
  -9.000  -0.8558   0.04164   0.03110  -0.0199   1.0000   0.0797
  -8.750  -0.8361   0.03975   0.02918  -0.0193   1.0000   0.0831
  -8.500  -0.8177   0.03799   0.02720  -0.0183   1.0000   0.0883
  -8.250  -0.7966   0.03616   0.02518  -0.0175   1.0000   0.0933
  -8.000  -0.7748   0.03467   0.02368  -0.0168   1.0000   0.0987
  -7.750  -0.7531   0.03325   0.02204  -0.0159   1.0000   0.1062
  -7.500  -0.7321   0.03191   0.02079  -0.0150   1.0000   0.1133
  -7.250  -0.7114   0.03065   0.01945  -0.0139   1.0000   0.1223
  -7.000  -0.6926   0.02946   0.01822  -0.0127   1.0000   0.1332
  -6.750  -0.6755   0.02823   0.01707  -0.0113   1.0000   0.1449
  -6.500  -0.6596   0.02701   0.01594  -0.0098   1.0000   0.1609
  -6.250  -0.6447   0.02576   0.01482  -0.0082   1.0000   0.1813
  -6.000  -0.6316   0.02445   0.01375  -0.0064   1.0000   0.2113
  -5.750  -0.6199   0.02309   0.01276  -0.0044   1.0000   0.2564
  -5.500  -0.6092   0.02190   0.01216  -0.0020   1.0000   0.3273
  -5.250  -0.5959   0.02133   0.01206   0.0008   1.0000   0.4083
  -5.000  -0.5803   0.02116   0.01208   0.0034   1.0000   0.4696
  -4.750  -0.5640   0.02113   0.01205   0.0060   1.0000   0.5136
  -4.500  -0.5478   0.02115   0.01208   0.0086   1.0000   0.5489
  -4.250  -0.5319   0.02121   0.01213   0.0112   1.0000   0.5788
  -4.000  -0.5175   0.02124   0.01213   0.0139   1.0000   0.6057
  -3.750  -0.5027   0.02136   0.01226   0.0168   1.0000   0.6284
  -3.500  -0.4905   0.02139   0.01227   0.0198   1.0000   0.6500
  -3.250  -0.4778   0.02139   0.01223   0.0223   0.9986   0.6703
  -3.000  -0.4390   0.02155   0.01232   0.0206   0.9821   0.6906
  -2.750  -0.4002   0.02159   0.01223   0.0186   0.9670   0.7081
  -2.500  -0.3608   0.02153   0.01205   0.0163   0.9529   0.7231
  -2.250  -0.3207   0.02143   0.01181   0.0138   0.9402   0.7369
  -2.000  -0.2783   0.02134   0.01163   0.0109   0.9290   0.7492
  -1.750  -0.2398   0.02125   0.01146   0.0089   0.9161   0.7597
  -1.500  -0.2036   0.02113   0.01124   0.0071   0.9034   0.7709
  -1.250  -0.1672   0.02104   0.01108   0.0054   0.8913   0.7819
  -1.000  -0.1285   0.02096   0.01096   0.0034   0.8808   0.7915
  -0.750  -0.0973   0.02089   0.01083   0.0026   0.8680   0.8025
  -0.500  -0.0650   0.02086   0.01077   0.0017   0.8562   0.8130
  -0.250  -0.0309   0.02083   0.01073   0.0006   0.8457   0.8232
   0.000   0.0001   0.02080   0.01069   0.0000   0.8345   0.8345
   0.250   0.0310   0.02083   0.01072  -0.0006   0.8231   0.8456
   0.500   0.0651   0.02086   0.01077  -0.0017   0.8130   0.8562
   0.750   0.0974   0.02089   0.01083  -0.0026   0.8025   0.8681
   1.000   0.1285   0.02097   0.01096  -0.0033   0.7915   0.8810
   1.250   0.1674   0.02104   0.01108  -0.0053   0.7818   0.8914
   1.500   0.2037   0.02113   0.01124  -0.0070   0.7708   0.9035
   1.750   0.2398   0.02125   0.01146  -0.0088   0.7596   0.9162
   2.000   0.2784   0.02134   0.01163  -0.0109   0.7491   0.9291
   2.250   0.3209   0.02143   0.01181  -0.0138   0.7369   0.9403
   2.500   0.3610   0.02153   0.01205  -0.0163   0.7231   0.9531
   2.750   0.4004   0.02158   0.01222  -0.0186   0.7080   0.9671
   3.000   0.4391   0.02155   0.01232  -0.0206   0.6907   0.9821
   3.250   0.4780   0.02139   0.01223  -0.0223   0.6703   0.9987
   3.500   0.4905   0.02139   0.01227  -0.0198   0.6499   1.0000
   3.750   0.5026   0.02135   0.01225  -0.0168   0.6282   1.0000
   4.000   0.5176   0.02123   0.01212  -0.0139   0.6055   1.0000
   4.250   0.5319   0.02121   0.01213  -0.0112   0.5787   1.0000
   4.500   0.5479   0.02116   0.01208  -0.0086   0.5489   1.0000
   4.750   0.5640   0.02113   0.01205  -0.0060   0.5135   1.0000
   5.000   0.5803   0.02116   0.01207  -0.0034   0.4690   1.0000
   5.250   0.5959   0.02133   0.01206  -0.0008   0.4081   1.0000
   5.500   0.6093   0.02190   0.01216   0.0020   0.3276   1.0000
   5.750   0.6199   0.02309   0.01276   0.0045   0.2565   1.0000
   6.000   0.6316   0.02445   0.01375   0.0064   0.2111   1.0000
   6.250   0.6448   0.02577   0.01483   0.0082   0.1812   1.0000
   6.500   0.6597   0.02702   0.01594   0.0098   0.1606   1.0000
   6.750   0.6756   0.02823   0.01708   0.0113   0.1450   1.0000
   7.000   0.6927   0.02947   0.01823   0.0127   0.1330   1.0000
   7.250   0.7115   0.03065   0.01945   0.0139   0.1222   1.0000
   7.500   0.7322   0.03192   0.02080   0.0150   0.1131   1.0000
   7.750   0.7531   0.03327   0.02204   0.0159   0.1060   1.0000
   8.000   0.7751   0.03469   0.02370   0.0168   0.0987   1.0000
   8.250   0.7968   0.03619   0.02520   0.0175   0.0933   1.0000
   8.500   0.8178   0.03800   0.02722   0.0183   0.0882   1.0000
   8.750   0.8363   0.03977   0.02919   0.0193   0.0831   1.0000
   9.000   0.8560   0.04166   0.03111   0.0199   0.0796   1.0000
   9.250   0.8708   0.04406   0.03384   0.0210   0.0766   1.0000
   9.500   0.8810   0.04657   0.03675   0.0224   0.0732   1.0000
   9.750   0.8910   0.04895   0.03937   0.0236   0.0703   1.0000
  10.000   0.9004   0.05149   0.04210   0.0247   0.0685   1.0000
  10.250   0.9115   0.05403   0.04468   0.0254   0.0666   1.0000
  10.500   0.9049   0.05744   0.04847   0.0271   0.0655   1.0000
  10.750   0.8903   0.06103   0.05242   0.0288   0.0646   1.0000
  11.000   0.8697   0.06473   0.05639   0.0302   0.0640   1.0000
  11.250   0.8482   0.06917   0.06103   0.0299   0.0639   1.0000
  11.500   0.8233   0.07459   0.06663   0.0278   0.0640   1.0000
  11.750   0.7941   0.08144   0.07362   0.0239   0.0642   1.0000
  12.000   0.7643   0.08977   0.08203   0.0186   0.0648   1.0000
  12.250   0.7374   0.09907   0.09137   0.0127   0.0653   1.0000
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