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LISSAMAN 7769 AIRFOIL (l7769-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: LISSAMAN 7769 AIRFOIL (l7769-il)
Reynolds number: 100,000
Max Cl/Cd: 39.84 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-l7769-il-100000-n5.txt
Download as CSV file: xf-l7769-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LISSAMAN 7769 AIRFOIL                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4065   0.11385   0.10783   0.0103   0.5753   0.0726
  -9.000  -0.4091   0.11104   0.10505   0.0069   0.5732   0.0731
  -8.750  -0.4090   0.10788   0.10191   0.0041   0.5710   0.0732
  -8.500  -0.4089   0.10458   0.09863   0.0013   0.5687   0.0734
  -8.250  -0.4099   0.10128   0.09534  -0.0016   0.5667   0.0735
  -8.000  -0.3853   0.09676   0.09074   0.0014   0.5636   0.0747
  -7.750  -0.3718   0.09374   0.08771   0.0016   0.5606   0.0759
  -7.500  -0.3667   0.09060   0.08460   0.0001   0.5579   0.0763
  -7.000  -0.3794   0.07747   0.07139  -0.0125   0.5552   0.0540
  -6.750  -0.3679   0.07425   0.06814  -0.0140   0.5527   0.0533
  -6.500  -0.3567   0.07051   0.06434  -0.0165   0.5505   0.0527
  -6.250  -0.3449   0.06634   0.06005  -0.0197   0.5487   0.0523
  -6.000  -0.3313   0.06181   0.05534  -0.0233   0.5470   0.0526
  -5.750  -0.3151   0.05725   0.05061  -0.0265   0.5449   0.0528
  -5.500  -0.2970   0.05298   0.04616  -0.0290   0.5423   0.0525
  -5.250  -0.2774   0.04876   0.04170  -0.0311   0.5396   0.0520
  -5.000  -0.2566   0.04440   0.03700  -0.0329   0.5372   0.0517
  -4.750  -0.2347   0.03995   0.03212  -0.0342   0.5348   0.0517
  -4.500  -0.2118   0.03576   0.02741  -0.0350   0.5327   0.0520
  -4.250  -0.1878   0.03181   0.02272  -0.0355   0.5309   0.0537
  -4.000  -0.1622   0.02956   0.02003  -0.0356   0.5285   0.0549
  -3.750  -0.1355   0.02838   0.01869  -0.0356   0.5257   0.0558
  -3.500  -0.1086   0.02722   0.01734  -0.0356   0.5230   0.0568
  -3.250  -0.0815   0.02614   0.01603  -0.0355   0.5205   0.0580
  -3.000  -0.0541   0.02511   0.01476  -0.0353   0.5181   0.0596
  -2.750  -0.0267   0.02415   0.01353  -0.0350   0.5160   0.0617
  -2.500   0.0006   0.02352   0.01276  -0.0347   0.5140   0.0645
  -2.250   0.0282   0.02325   0.01249  -0.0346   0.5114   0.0680
  -2.000   0.0562   0.02273   0.01189  -0.0345   0.5085   0.0725
  -1.750   0.0837   0.02237   0.01157  -0.0344   0.5060   0.0768
  -1.500   0.1113   0.02203   0.01119  -0.0341   0.5037   0.0843
  -1.250   0.1387   0.02190   0.01110  -0.0340   0.5016   0.0940
  -1.000   0.1663   0.02186   0.01105  -0.0337   0.4997   0.1069
  -0.750   0.1937   0.02183   0.01095  -0.0335   0.4979   0.1196
  -0.500   0.2212   0.02190   0.01097  -0.0333   0.4961   0.1339
  -0.250   0.2488   0.02209   0.01125  -0.0335   0.4929   0.1503
   0.000   0.2760   0.02209   0.01133  -0.0334   0.4902   0.1627
   0.250   0.3032   0.02211   0.01132  -0.0333   0.4880   0.1719
   0.500   0.3299   0.02204   0.01133  -0.0331   0.4859   0.1814
   0.750   0.3571   0.02203   0.01133  -0.0329   0.4841   0.1920
   1.000   0.3844   0.02205   0.01131  -0.0327   0.4824   0.2035
   1.250   0.4117   0.02202   0.01129  -0.0324   0.4808   0.2194
   1.500   0.4390   0.02209   0.01151  -0.0325   0.4786   0.2469
   1.750   0.4802   0.02056   0.01205  -0.0353   0.4752   1.0000
   2.000   0.5067   0.02106   0.01247  -0.0353   0.4727   1.0000
   2.250   0.5331   0.02152   0.01284  -0.0351   0.4704   1.0000
   2.500   0.5595   0.02188   0.01311  -0.0349   0.4682   1.0000
   2.750   0.5859   0.02218   0.01331  -0.0345   0.4663   1.0000
   3.000   0.6124   0.02246   0.01350  -0.0342   0.4647   1.0000
   3.250   0.6388   0.02277   0.01373  -0.0338   0.4634   1.0000
   3.500   0.6634   0.02387   0.01498  -0.0344   0.4591   1.0000
   3.750   0.6886   0.02456   0.01571  -0.0345   0.4556   1.0000
   4.000   0.7142   0.02506   0.01622  -0.0344   0.4530   1.0000
   4.250   0.7401   0.02542   0.01656  -0.0341   0.4508   1.0000
   4.500   0.7665   0.02562   0.01672  -0.0336   0.4489   1.0000
   4.750   0.7934   0.02564   0.01667  -0.0330   0.4472   1.0000
   5.000   0.8148   0.02699   0.01825  -0.0337   0.4395   1.0000
   5.250   0.8407   0.02714   0.01842  -0.0333   0.4360   1.0000
   5.500   0.8675   0.02708   0.01832  -0.0326   0.4335   1.0000
   5.750   0.8948   0.02697   0.01817  -0.0319   0.4317   1.0000
   6.000   0.9137   0.02866   0.02011  -0.0327   0.4243   1.0000
   6.250   0.9386   0.02897   0.02048  -0.0323   0.4206   1.0000
   6.500   0.9654   0.02888   0.02040  -0.0317   0.4181   1.0000
   6.750   0.9935   0.02853   0.02004  -0.0309   0.4161   1.0000
   7.000   1.0091   0.03042   0.02222  -0.0316   0.4073   1.0000
   7.250   1.0359   0.03017   0.02199  -0.0309   0.4038   1.0000
   7.500   1.0660   0.02932   0.02113  -0.0298   0.4012   1.0000
   7.750   1.0816   0.03083   0.02289  -0.0302   0.3917   1.0000
   8.000   1.1106   0.03009   0.02217  -0.0293   0.3878   1.0000
   8.500   1.1537   0.03093   0.02329  -0.0286   0.3743   1.0000
   8.750   1.1844   0.02999   0.02237  -0.0276   0.3709   1.0000
   9.000   1.1944   0.03190   0.02454  -0.0279   0.3601   1.0000
   9.250   1.2262   0.03078   0.02344  -0.0268   0.3560   1.0000
   9.500   1.2325   0.03291   0.02582  -0.0272   0.3440   1.0000
   9.750   1.2352   0.03535   0.02843  -0.0277   0.3321   1.0000
  10.000   1.2232   0.03955   0.03272  -0.0294   0.3186   1.0000
  10.250   1.2602   0.03760   0.03083  -0.0277   0.3129   1.0000
  10.500   1.2438   0.04168   0.03493  -0.0284   0.2996   1.0000
  10.750   1.2418   0.04422   0.03750  -0.0283   0.2876   1.0000
  11.000   1.2521   0.04536   0.03864  -0.0278   0.2770   1.0000
  11.250   1.2738   0.04509   0.03837  -0.0267   0.2675   1.0000
  11.500   1.2847   0.04610   0.03935  -0.0260   0.2568   1.0000
  11.750   1.2881   0.04806   0.04129  -0.0256   0.2458   1.0000
  12.000   1.2934   0.04974   0.04292  -0.0252   0.2345   1.0000
  12.250   1.2975   0.05153   0.04461  -0.0247   0.2228   1.0000
  12.500   1.2970   0.05394   0.04696  -0.0246   0.2111   1.0000
  12.750   1.2896   0.05740   0.05042  -0.0252   0.1994   1.0000
  13.000   1.2839   0.06067   0.05367  -0.0256   0.1881   1.0000
  13.250   1.2788   0.06392   0.05687  -0.0262   0.1771   1.0000
  13.500   1.2742   0.06727   0.06020  -0.0269   0.1668   1.0000
  13.750   1.2696   0.07097   0.06397  -0.0279   0.1573   1.0000
  14.000   1.2689   0.07412   0.06713  -0.0286   0.1493   1.0000
  14.250   1.2667   0.07766   0.07072  -0.0295   0.1412   1.0000
  14.500   1.2649   0.08120   0.07432  -0.0305   0.1335   1.0000
  14.750   1.2620   0.08492   0.07804  -0.0316   0.1256   1.0000
  15.000   1.2582   0.08899   0.08222  -0.0330   0.1174   1.0000
  15.250   1.2532   0.09327   0.08652  -0.0345   0.1091   1.0000
  15.500   1.2476   0.09776   0.09108  -0.0361   0.1006   1.0000
  15.750   1.2416   0.10246   0.09585  -0.0379   0.0917   1.0000
  16.000   1.2340   0.10750   0.10093  -0.0400   0.0826   1.0000
  16.250   1.2255   0.11281   0.10625  -0.0422   0.0737   1.0000
  16.500   1.2160   0.11841   0.11183  -0.0447   0.0657   1.0000
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