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LIEBECK L1003 AIRFOIL (l1003-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: LIEBECK L1003 AIRFOIL (l1003-il)
Reynolds number: 500,000
Max Cl/Cd: 68.26 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-l1003-il-500000-n5.txt
Download as CSV file: xf-l1003-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LIEBECK L1003 AIRFOIL                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.1538   0.09320   0.08853   0.0093   0.3819   0.0397
  -6.750  -0.1470   0.09044   0.08578   0.0078   0.3816   0.0394
  -6.500  -0.1412   0.08762   0.08297   0.0063   0.3812   0.0393
  -6.250  -0.1359   0.08482   0.08020   0.0049   0.3809   0.0392
  -6.000  -0.1314   0.08207   0.07746   0.0034   0.3806   0.0392
  -5.750  -0.1286   0.07933   0.07474   0.0021   0.3803   0.0391
  -5.500  -0.1301   0.07675   0.07220   0.0010   0.3801   0.0390
  -5.250  -0.1275   0.07380   0.06926  -0.0015   0.3798   0.0390
  -5.000  -0.1204   0.07061   0.06608  -0.0047   0.3795   0.0392
  -4.750  -0.1111   0.06712   0.06256  -0.0085   0.3791   0.0396
  -4.500  -0.0995   0.06340   0.05882  -0.0123   0.3788   0.0396
  -4.250  -0.0853   0.05950   0.05486  -0.0162   0.3785   0.0397
  -4.000  -0.0687   0.05536   0.05063  -0.0201   0.3782   0.0399
  -3.750  -0.0502   0.05061   0.04575  -0.0241   0.3779   0.0401
  -3.500  -0.0300   0.04518   0.04011  -0.0280   0.3776   0.0405
  -2.000   0.1181   0.02202   0.01511  -0.0359   0.3751   0.0453
  -1.500   0.1759   0.02148   0.01448  -0.0360   0.3737   0.0457
  -1.250   0.2048   0.02119   0.01413  -0.0361   0.3730   0.0460
  -0.750   0.2611   0.01800   0.01039  -0.0362   0.3722   0.0497
  -0.500   0.2905   0.01807   0.01046  -0.0363   0.3718   0.0499
  -0.250   0.3199   0.01811   0.01050  -0.0363   0.3714   0.0501
   0.000   0.3491   0.01813   0.01050  -0.0364   0.3706   0.0505
   0.250   0.3783   0.01811   0.01045  -0.0365   0.3697   0.0509
   0.500   0.4075   0.01793   0.01024  -0.0366   0.3691   0.0517
   0.750   0.4364   0.01692   0.00905  -0.0365   0.3686   0.0543
   1.000   0.4660   0.01696   0.00912  -0.0366   0.3681   0.0547
   1.250   0.4954   0.01697   0.00915  -0.0367   0.3675   0.0551
   1.500   0.5249   0.01692   0.00912  -0.0369   0.3667   0.0558
   1.750   0.5544   0.01674   0.00892  -0.0369   0.3653   0.0572
   2.000   0.5838   0.01638   0.00848  -0.0370   0.3636   0.0592
   2.250   0.6133   0.01631   0.00843  -0.0371   0.3617   0.0598
   2.500   0.6428   0.01622   0.00834  -0.0372   0.3601   0.0606
   2.750   0.6721   0.01612   0.00822  -0.0373   0.3590   0.0617
   3.000   0.7013   0.01597   0.00802  -0.0373   0.3579   0.0632
   3.250   0.7305   0.01586   0.00787  -0.0374   0.3568   0.0643
   3.500   0.7595   0.01582   0.00785  -0.0375   0.3556   0.0651
   3.750   0.7885   0.01582   0.00785  -0.0377   0.3543   0.0662
   4.000   0.8176   0.01581   0.00787  -0.0378   0.3534   0.0675
   4.250   0.8467   0.01583   0.00789  -0.0380   0.3523   0.0689
   4.500   0.8755   0.01578   0.00789  -0.0381   0.3509   0.0697
   4.750   0.9043   0.01576   0.00793  -0.0383   0.3493   0.0704
   5.000   0.9331   0.01574   0.00797  -0.0385   0.3468   0.0714
   5.250   0.9620   0.01573   0.00797  -0.0387   0.3440   0.0724
   5.500   0.9907   0.01574   0.00797  -0.0389   0.3417   0.0731
   5.750   1.0192   0.01579   0.00802  -0.0391   0.3395   0.0738
   6.000   1.0476   0.01591   0.00820  -0.0393   0.3375   0.0744
   6.250   1.0759   0.01607   0.00841  -0.0395   0.3343   0.0749
   6.500   1.1038   0.01617   0.00856  -0.0398   0.3285   0.0759
   6.750   1.1264   0.01775   0.00997  -0.0415   0.2777   0.0767
   7.000   1.0575   0.03232   0.02490  -0.0523   0.2498   0.0758
   7.250   0.9900   0.03817   0.03080  -0.0485   0.2486   0.0751
   7.500   0.9502   0.04353   0.03621  -0.0472   0.2449   0.0748
   7.750   0.8962   0.05082   0.04354  -0.0466   0.2357   0.0745
   8.250   0.8582   0.05960   0.05230  -0.0466   0.2215   0.0746
   8.500   0.8541   0.06267   0.05536  -0.0466   0.2163   0.0748
   8.750   0.8544   0.06532   0.05801  -0.0466   0.2121   0.0751
   9.000   0.8614   0.06726   0.05996  -0.0466   0.2092   0.0758
   9.250   0.8706   0.06900   0.06172  -0.0466   0.2058   0.0764
   9.500   0.8793   0.07083   0.06355  -0.0466   0.2015   0.0770
   9.750   0.8884   0.07266   0.06537  -0.0466   0.1983   0.0773
  10.000   0.8967   0.07460   0.06730  -0.0467   0.1952   0.0779
  10.250   0.9082   0.07621   0.06893  -0.0467   0.1928   0.0783
  10.500   0.9193   0.07788   0.07062  -0.0468   0.1896   0.0789
  10.750   0.9303   0.07958   0.07233  -0.0469   0.1858   0.0794
  11.000   0.9389   0.08158   0.07430  -0.0471   0.1806   0.0799
  11.250   0.9484   0.08350   0.07619  -0.0473   0.1695   0.0804
  11.500   0.9394   0.08768   0.08005  -0.0481   0.1238   0.0806
  11.750   0.9493   0.08958   0.08191  -0.0484   0.1175   0.0810
  12.000   0.9606   0.09131   0.08363  -0.0486   0.1131   0.0819
  12.250   0.9723   0.09302   0.08534  -0.0488   0.1101   0.0830
  12.500   0.9846   0.09467   0.08701  -0.0491   0.1085   0.0844
  12.750   0.9949   0.09662   0.08896  -0.0494   0.1056   0.0855
  13.000   1.0063   0.09843   0.09079  -0.0497   0.1040   0.0867
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