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LIEBECK L1003 AIRFOIL (l1003-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: LIEBECK L1003 AIRFOIL (l1003-il)
Reynolds number: 500,000
Max Cl/Cd: 74.15 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-l1003-il-500000.txt
Download as CSV file: xf-l1003-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1979   0.11624   0.11181   0.0207   0.4057   0.0462
  -8.500  -0.1948   0.11327   0.10885   0.0179   0.4054   0.0471
  -8.250  -0.2133   0.11024   0.10586   0.0117   0.4053   0.0474
  -8.000  -0.1965   0.10688   0.10250   0.0117   0.4048   0.0475
  -7.750  -0.1800   0.10396   0.09959   0.0117   0.4043   0.0476
  -7.500  -0.1667   0.10135   0.09699   0.0111   0.4038   0.0478
  -7.250  -0.1546   0.09890   0.09456   0.0104   0.4033   0.0479
  -7.000  -0.1437   0.09655   0.09221   0.0094   0.4029   0.0482
  -6.750  -0.1337   0.09421   0.08990   0.0083   0.4025   0.0484
  -6.500  -0.1243   0.09190   0.08760   0.0072   0.4020   0.0488
  -6.250  -0.1155   0.08956   0.08528   0.0060   0.4016   0.0492
  -6.000  -0.1077   0.08719   0.08293   0.0047   0.4012   0.0496
  -5.750  -0.1007   0.08481   0.08057   0.0033   0.4008   0.0502
  -5.500  -0.0960   0.08236   0.07815   0.0019   0.4005   0.0509
  -5.250  -0.1213   0.07748   0.07327  -0.0108   0.4005   0.0521
  -5.000  -0.1097   0.07392   0.06971  -0.0131   0.4002   0.0522
  -4.750  -0.0941   0.07164   0.06745  -0.0128   0.3997   0.0523
  -4.500  -0.0781   0.06945   0.06526  -0.0132   0.3993   0.0524
  -4.250  -0.0618   0.06728   0.06308  -0.0141   0.3989   0.0526
  -4.000  -0.0447   0.06507   0.06087  -0.0155   0.3985   0.0529
  -3.750  -0.0267   0.06284   0.05863  -0.0173   0.3982   0.0532
  -3.500  -0.0074   0.06055   0.05631  -0.0193   0.3978   0.0537
  -3.250   0.0132   0.05817   0.05389  -0.0216   0.3975   0.0544
  -3.000   0.0472   0.05245   0.04773  -0.0305   0.3972   0.0570
  -2.750   0.0686   0.04937   0.04458  -0.0319   0.3968   0.0571
  -2.500   0.0901   0.04752   0.04274  -0.0324   0.3965   0.0573
  -2.250   0.1129   0.04595   0.04117  -0.0330   0.3961   0.0575
  -2.000   0.1365   0.04454   0.03974  -0.0336   0.3957   0.0578
  -1.750   0.1610   0.04319   0.03834  -0.0342   0.3952   0.0582
  -1.500   0.1866   0.04190   0.03699  -0.0351   0.3944   0.0589
  -1.250   0.2232   0.03933   0.03386  -0.0371   0.3935   0.0621
  -1.000   0.2481   0.03724   0.03173  -0.0381   0.3929   0.0624
  -0.750   0.2734   0.03591   0.03044  -0.0386   0.3926   0.0626
  -0.500   0.2994   0.03494   0.02949  -0.0391   0.3924   0.0629
  -0.250   0.3261   0.03408   0.02863  -0.0396   0.3921   0.0634
   0.000   0.3534   0.03327   0.02778  -0.0401   0.3917   0.0641
   0.250   0.3814   0.03242   0.02688  -0.0405   0.3913   0.0653
   0.500   0.4132   0.03059   0.02460  -0.0407   0.3909   0.0681
   0.750   0.4398   0.02998   0.02407  -0.0412   0.3903   0.0686
   1.000   0.4670   0.02950   0.02361  -0.0416   0.3895   0.0693
   1.250   0.4948   0.02900   0.02308  -0.0419   0.3887   0.0705
   1.500   0.5252   0.02803   0.02171  -0.0417   0.3878   0.0742
   1.750   0.5527   0.02724   0.02097  -0.0419   0.3868   0.0748
   2.000   0.5810   0.02659   0.02029  -0.0420   0.3858   0.0760
   2.250   0.6108   0.02601   0.01943  -0.0418   0.3849   0.0808
   2.500   0.6385   0.02534   0.01881  -0.0420   0.3841   0.0819
   2.750   0.6672   0.02514   0.01846  -0.0419   0.3834   0.0881
   3.000   0.6955   0.02445   0.01781  -0.0420   0.3827   0.0901
   3.250   0.7246   0.02389   0.01713  -0.0418   0.3819   0.0970
   3.500   0.7561   0.02247   0.01527  -0.0409   0.3812   0.0807
   3.750   0.7850   0.02182   0.01466  -0.0408   0.3802   0.0837
   4.000   0.8135   0.02161   0.01436  -0.0406   0.3792   0.0851
   4.250   0.8394   0.02212   0.01486  -0.0408   0.3779   0.0856
   4.500   0.8677   0.02203   0.01478  -0.0409   0.3774   0.0864
   4.750   0.8954   0.02193   0.01470  -0.0410   0.3769   0.0879
   5.000   0.9225   0.02186   0.01472  -0.0412   0.3762   0.0890
   5.250   0.9494   0.02193   0.01488  -0.0414   0.3754   0.0897
   5.500   0.9762   0.02207   0.01508  -0.0415   0.3746   0.0910
   5.750   1.0026   0.02227   0.01535  -0.0417   0.3737   0.0923
   6.000   1.0291   0.02240   0.01553  -0.0419   0.3726   0.0930
   6.250   1.0563   0.02240   0.01557  -0.0420   0.3714   0.0936
   6.500   1.0843   0.02227   0.01545  -0.0420   0.3703   0.0943
   6.750   1.1143   0.02177   0.01494  -0.0418   0.3691   0.0955
   7.000   1.1462   0.02093   0.01405  -0.0416   0.3678   0.0971
   7.250   1.1784   0.02012   0.01317  -0.0413   0.3664   0.0983
   7.500   1.2085   0.01972   0.01272  -0.0412   0.3651   0.0997
   7.750   1.2365   0.01973   0.01271  -0.0412   0.3638   0.1012
   8.000   1.2627   0.02001   0.01304  -0.0414   0.3628   0.1028
   8.250   1.2879   0.02034   0.01349  -0.0417   0.3619   0.1059
   8.500   1.3123   0.02077   0.01403  -0.0420   0.3607   0.1100
   8.750   1.3362   0.02124   0.01460  -0.0423   0.3593   0.1165
   9.000   1.3651   0.02025   0.01526  -0.0438   0.3577   1.0000
   9.250   1.3898   0.02065   0.01568  -0.0441   0.3562   1.0000
   9.500   1.4166   0.02076   0.01578  -0.0443   0.3544   1.0000
   9.750   1.4455   0.02059   0.01557  -0.0444   0.3524   1.0000
  10.000   1.4778   0.01993   0.01479  -0.0443   0.3499   1.0000
  10.250   1.4913   0.02185   0.01687  -0.0458   0.3475   1.0000
  11.500   0.9343   0.09223   0.08648  -0.0510   0.2769   0.1032
  11.750   0.9675   0.09093   0.08515  -0.0505   0.2719   0.1079
  12.000   1.0050   0.08908   0.08326  -0.0498   0.2681   0.1147
  12.250   1.0869   0.08521   0.08097  -0.0554   0.2622   1.0000
  12.500   1.1317   0.08244   0.07796  -0.0546   0.2522   1.0000
  12.750   1.1459   0.08344   0.07873  -0.0545   0.2395   1.0000
  13.000   1.1530   0.08545   0.08066  -0.0546   0.2321   1.0000
  13.250   1.1595   0.08756   0.08268  -0.0548   0.2256   1.0000
  13.500   1.1686   0.08946   0.08456  -0.0549   0.2218   1.0000
  13.750   1.1768   0.09144   0.08651  -0.0551   0.2181   1.0000
  14.000   1.1842   0.09351   0.08853  -0.0553   0.2137   1.0000
  14.250   1.1937   0.09536   0.09036  -0.0554   0.2101   1.0000
  14.500   1.2037   0.09719   0.09222  -0.0556   0.2069   1.0000
  14.750   1.2139   0.09900   0.09402  -0.0558   0.2033   1.0000
  15.000   1.2229   0.10094   0.09593  -0.0561   0.1993   1.0000
  15.250   1.2331   0.10270   0.09767  -0.0563   0.1962   1.0000
  15.500   1.2440   0.10446   0.09947  -0.0565   0.1925   1.0000
  15.750   1.2534   0.10639   0.10140  -0.0569   0.1875   1.0000
  16.000   1.2601   0.10869   0.10368  -0.0573   0.1809   1.0000
  16.250   1.2643   0.11140   0.10636  -0.0579   0.1680   1.0000
  16.500   1.2474   0.11707   0.11174  -0.0593   0.1317   1.0000
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