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FX 79-L-120 (fx79l120-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 79-L-120 (fx79l120-il)
Reynolds number: 100,000
Max Cl/Cd: 40.93 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx79l120-il-100000.txt
Download as CSV file: xf-fx79l120-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5916   0.09233   0.08741  -0.0162   1.0000   0.1063
 -11.250  -0.5684   0.09158   0.08664  -0.0133   1.0000   0.1080
 -11.000  -0.8801   0.06995   0.06414  -0.0299   1.0000   0.0782
 -10.750  -0.8880   0.06520   0.05931  -0.0291   1.0000   0.0774
 -10.500  -0.9024   0.06088   0.05478  -0.0276   1.0000   0.0770
 -10.250  -0.9107   0.05669   0.05036  -0.0261   1.0000   0.0763
 -10.000  -0.9176   0.05256   0.04591  -0.0242   1.0000   0.0761
  -9.750  -0.9196   0.04877   0.04174  -0.0223   1.0000   0.0761
  -9.500  -0.9185   0.04554   0.03805  -0.0201   1.0000   0.0772
  -9.250  -0.9139   0.04303   0.03499  -0.0177   1.0000   0.0785
  -9.000  -0.9010   0.03918   0.03100  -0.0168   1.0000   0.0808
  -8.750  -0.8833   0.03682   0.02849  -0.0158   1.0000   0.0829
  -8.500  -0.8655   0.03482   0.02629  -0.0146   1.0000   0.0863
  -8.250  -0.8488   0.03303   0.02410  -0.0129   1.0000   0.0902
  -8.000  -0.8287   0.03063   0.02148  -0.0119   1.0000   0.0936
  -7.750  -0.8065   0.02898   0.01982  -0.0112   1.0000   0.0986
  -7.500  -0.7852   0.02769   0.01828  -0.0101   1.0000   0.1045
  -7.250  -0.7611   0.02581   0.01648  -0.0095   1.0000   0.1103
  -7.000  -0.7391   0.02470   0.01525  -0.0085   1.0000   0.1184
  -6.750  -0.7164   0.02323   0.01392  -0.0077   1.0000   0.1269
  -6.500  -0.6947   0.02202   0.01272  -0.0066   1.0000   0.1373
  -6.250  -0.6742   0.02095   0.01172  -0.0053   1.0000   0.1506
  -6.000  -0.6561   0.01975   0.01075  -0.0037   1.0000   0.1676
  -5.750  -0.6400   0.01861   0.00984  -0.0018   1.0000   0.1924
  -5.500  -0.6282   0.01721   0.00889   0.0007   1.0000   0.2359
  -5.250  -0.6238   0.01553   0.00814   0.0043   1.0000   0.3461
  -5.000  -0.6149   0.01502   0.00827   0.0080   1.0000   0.4692
  -4.750  -0.6005   0.01512   0.00846   0.0110   1.0000   0.5255
  -4.500  -0.5864   0.01530   0.00866   0.0138   1.0000   0.5593
  -4.250  -0.5750   0.01551   0.00887   0.0170   1.0000   0.5858
  -4.000  -0.5649   0.01572   0.00909   0.0201   1.0000   0.6073
  -3.750  -0.5542   0.01596   0.00934   0.0230   1.0000   0.6266
  -3.500  -0.5346   0.01625   0.00962   0.0242   0.9971   0.6478
  -3.250  -0.4896   0.01660   0.00991   0.0210   0.9848   0.6725
  -3.000  -0.4458   0.01695   0.01028   0.0185   0.9735   0.6951
  -2.750  -0.4036   0.01717   0.01045   0.0161   0.9621   0.7168
  -2.500  -0.3622   0.01731   0.01057   0.0140   0.9514   0.7361
  -2.250  -0.3141   0.01740   0.01061   0.0106   0.9441   0.7528
  -2.000  -0.2755   0.01738   0.01057   0.0088   0.9328   0.7666
  -1.750  -0.2341   0.01735   0.01052   0.0066   0.9231   0.7776
  -1.500  -0.1914   0.01724   0.01035   0.0039   0.9143   0.7888
  -1.250  -0.1597   0.01714   0.01019   0.0030   0.9023   0.8007
  -1.000  -0.1224   0.01710   0.01015   0.0016   0.8924   0.8096
  -0.750  -0.0879   0.01699   0.01000   0.0004   0.8824   0.8198
  -0.500  -0.0607   0.01696   0.00996   0.0006   0.8705   0.8305
  -0.250  -0.0284   0.01695   0.00994   0.0000   0.8607   0.8395
   0.000   0.0000   0.01690   0.00988   0.0000   0.8506   0.8506
   0.250   0.0285   0.01695   0.00994   0.0000   0.8395   0.8606
   0.500   0.0607   0.01696   0.00996  -0.0005   0.8302   0.8706
   0.750   0.0880   0.01699   0.01000  -0.0004   0.8197   0.8824
   1.000   0.1225   0.01710   0.01015  -0.0016   0.8096   0.8924
   1.250   0.1598   0.01714   0.01019  -0.0030   0.8007   0.9023
   1.500   0.1914   0.01724   0.01035  -0.0038   0.7888   0.9143
   1.750   0.2342   0.01735   0.01052  -0.0066   0.7777   0.9232
   2.000   0.2757   0.01739   0.01057  -0.0088   0.7668   0.9328
   2.250   0.3146   0.01740   0.01062  -0.0107   0.7528   0.9441
   2.500   0.3627   0.01732   0.01058  -0.0141   0.7362   0.9517
   2.750   0.4040   0.01717   0.01045  -0.0162   0.7167   0.9622
   3.000   0.4459   0.01694   0.01027  -0.0185   0.6948   0.9735
   3.250   0.4897   0.01660   0.00991  -0.0210   0.6724   0.9848
   3.500   0.5346   0.01624   0.00959  -0.0242   0.6471   0.9971
   3.750   0.5542   0.01596   0.00933  -0.0229   0.6264   1.0000
   4.000   0.5649   0.01573   0.00909  -0.0201   0.6073   1.0000
   4.250   0.5750   0.01551   0.00887  -0.0169   0.5857   1.0000
   4.500   0.5864   0.01530   0.00866  -0.0138   0.5592   1.0000
   4.750   0.6005   0.01512   0.00845  -0.0109   0.5252   1.0000
   5.000   0.6148   0.01502   0.00827  -0.0080   0.4686   1.0000
   5.250   0.6238   0.01553   0.00814  -0.0042   0.3454   1.0000
   5.500   0.6283   0.01721   0.00889  -0.0007   0.2361   1.0000
   5.750   0.6401   0.01861   0.00985   0.0018   0.1924   1.0000
   6.000   0.6561   0.01975   0.01074   0.0037   0.1673   1.0000
   6.250   0.6743   0.02095   0.01172   0.0053   0.1505   1.0000
   6.500   0.6947   0.02203   0.01272   0.0066   0.1371   1.0000
   6.750   0.7164   0.02323   0.01393   0.0077   0.1267   1.0000
   7.000   0.7391   0.02469   0.01526   0.0085   0.1181   1.0000
   7.250   0.7612   0.02582   0.01649   0.0095   0.1102   1.0000
   7.500   0.7852   0.02770   0.01830   0.0101   0.1044   1.0000
   7.750   0.8066   0.02902   0.01987   0.0113   0.0985   1.0000
   8.000   0.8288   0.03065   0.02150   0.0120   0.0936   1.0000
   8.250   0.8488   0.03305   0.02412   0.0130   0.0902   1.0000
   8.500   0.8656   0.03483   0.02630   0.0146   0.0863   1.0000
   8.750   0.8834   0.03683   0.02850   0.0158   0.0830   1.0000
   9.000   0.9012   0.03922   0.03104   0.0167   0.0806   1.0000
   9.250   0.9146   0.04326   0.03519   0.0175   0.0786   1.0000
   9.500   0.9186   0.04558   0.03809   0.0201   0.0772   1.0000
   9.750   0.9192   0.04881   0.04179   0.0223   0.0760   1.0000
  10.000   0.9169   0.05264   0.04601   0.0243   0.0760   1.0000
  10.250   0.9110   0.05669   0.05037   0.0261   0.0763   1.0000
  10.500   0.9019   0.06092   0.05484   0.0276   0.0769   1.0000
  10.750   0.8913   0.06537   0.05946   0.0288   0.0776   1.0000
  11.000   0.8795   0.07002   0.06422   0.0299   0.0782   1.0000
  11.250   0.6977   0.09835   0.09311   0.0092   0.1079   1.0000
  11.500   0.7267   0.09788   0.09267   0.0143   0.1064   1.0000
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