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LIEBECK L1003 AIRFOIL (l1003-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: LIEBECK L1003 AIRFOIL (l1003-il)
Reynolds number: 1,000,000
Max Cl/Cd: 104.1 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-l1003-il-1000000.txt
Download as CSV file: xf-l1003-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.1430   0.09028   0.08650   0.0086   0.3841   0.0406
  -6.500  -0.1352   0.08781   0.08404   0.0073   0.3838   0.0411
  -6.250  -0.1292   0.08515   0.08139   0.0058   0.3834   0.0420
  -6.000  -0.1584   0.08074   0.07703   0.0009   0.3834   0.0429
  -5.750  -0.1570   0.07722   0.07352  -0.0029   0.3831   0.0429
  -5.500  -0.1534   0.07262   0.06891  -0.0070   0.3829   0.0430
  -5.250  -0.1404   0.07010   0.06639  -0.0078   0.3824   0.0432
  -5.000  -0.1253   0.06793   0.06422  -0.0088   0.3820   0.0433
  -4.750  -0.1093   0.06586   0.06214  -0.0100   0.3815   0.0434
  -4.500  -0.0924   0.06381   0.06008  -0.0115   0.3810   0.0436
  -4.250  -0.0748   0.06166   0.05791  -0.0133   0.3804   0.0439
  -4.000  -0.0563   0.05936   0.05559  -0.0155   0.3799   0.0442
  -3.750  -0.0367   0.05701   0.05320  -0.0177   0.3793   0.0446
  -3.500  -0.0157   0.05462   0.05078  -0.0201   0.3784   0.0453
  -3.000   0.0329   0.04299   0.03873  -0.0301   0.3777   0.0477
  -2.750   0.0566   0.04129   0.03700  -0.0308   0.3775   0.0478
  -2.500   0.0814   0.03981   0.03549  -0.0314   0.3772   0.0480
  -2.250   0.0926   0.01781   0.01171  -0.0360   0.3773   0.0476
  -2.000   0.1222   0.01775   0.01163  -0.0360   0.3769   0.0479
  -1.750   0.1519   0.01786   0.01176  -0.0360   0.3766   0.0480
  -1.500   0.1815   0.01797   0.01189  -0.0361   0.3763   0.0482
  -1.250   0.2112   0.01808   0.01202  -0.0361   0.3759   0.0484
  -1.000   0.2407   0.01813   0.01209  -0.0362   0.3755   0.0486
  -0.750   0.2702   0.01813   0.01210  -0.0362   0.3751   0.0490
  -0.500   0.2996   0.01798   0.01193  -0.0363   0.3746   0.0495
  -0.250   0.3270   0.01498   0.00844  -0.0362   0.3741   0.0526
   0.000   0.3568   0.01503   0.00850  -0.0363   0.3734   0.0529
   0.250   0.3866   0.01509   0.00858  -0.0363   0.3728   0.0532
   0.500   0.4163   0.01513   0.00863  -0.0364   0.3723   0.0536
   0.750   0.4459   0.01512   0.00863  -0.0365   0.3719   0.0542
   1.000   0.4755   0.01491   0.00838  -0.0365   0.3713   0.0552
   1.250   0.5049   0.01425   0.00756  -0.0365   0.3705   0.0574
   1.500   0.5346   0.01416   0.00748  -0.0366   0.3696   0.0578
   1.750   0.5644   0.01413   0.00745  -0.0367   0.3686   0.0584
   2.000   0.5941   0.01412   0.00746  -0.0368   0.3677   0.0591
   2.250   0.6237   0.01405   0.00737  -0.0368   0.3669   0.0605
   2.500   0.6534   0.01407   0.00729  -0.0369   0.3661   0.0622
   2.750   0.6824   0.01379   0.00702  -0.0370   0.3649   0.0632
   3.000   0.7113   0.01395   0.00720  -0.0372   0.3634   0.0640
   3.250   0.7408   0.01387   0.00715  -0.0373   0.3630   0.0651
   3.500   0.7705   0.01374   0.00701  -0.0374   0.3627   0.0666
   3.750   0.8002   0.01362   0.00686  -0.0375   0.3623   0.0682
   4.000   0.8295   0.01339   0.00670  -0.0377   0.3617   0.0694
   4.250   0.8591   0.01324   0.00659  -0.0378   0.3607   0.0705
   4.500   0.8887   0.01310   0.00646  -0.0379   0.3597   0.0717
   4.750   0.9184   0.01304   0.00640  -0.0380   0.3586   0.0731
   5.000   0.9478   0.01288   0.00624  -0.0381   0.3575   0.0742
   5.250   0.9769   0.01268   0.00608  -0.0383   0.3564   0.0751
   5.500   1.0063   0.01257   0.00601  -0.0384   0.3553   0.0761
   5.750   1.0356   0.01251   0.00597  -0.0386   0.3542   0.0773
   6.000   1.0649   0.01246   0.00592  -0.0388   0.3528   0.0781
   6.250   1.0940   0.01246   0.00591  -0.0390   0.3507   0.0787
   6.500   1.1229   0.01251   0.00598  -0.0392   0.3489   0.0794
   6.750   1.1524   0.01249   0.00600  -0.0394   0.3477   0.0800
   7.000   1.1816   0.01240   0.00596  -0.0396   0.3460   0.0812
   7.250   1.2108   0.01239   0.00598  -0.0398   0.3436   0.0821
   7.500   1.2399   0.01241   0.00603  -0.0400   0.3409   0.0830
   7.750   1.2688   0.01249   0.00611  -0.0403   0.3373   0.0839
   8.000   1.2975   0.01262   0.00625  -0.0406   0.3342   0.0849
   8.250   1.3262   0.01274   0.00640  -0.0409   0.3282   0.0860
   8.500   1.3165   0.02147   0.01499  -0.0467   0.2402   0.0863
   8.750   1.2468   0.03188   0.02571  -0.0516   0.2445   0.0853
   9.000   1.1852   0.03710   0.03099  -0.0473   0.2449   0.0847
   9.250   1.1247   0.04408   0.03802  -0.0456   0.2392   0.0841
   9.500   1.0619   0.05225   0.04621  -0.0451   0.2303   0.0832
   9.750   1.0378   0.05712   0.05108  -0.0451   0.2237   0.0832
  10.000   1.0238   0.06121   0.05519  -0.0453   0.2190   0.0833
  10.250   1.0205   0.06425   0.05821  -0.0454   0.2147   0.0839
  10.500   1.0197   0.06711   0.06108  -0.0455   0.2106   0.0841
  10.750   1.0229   0.06961   0.06359  -0.0457   0.2079   0.0849
  11.000   1.0296   0.07170   0.06570  -0.0458   0.2049   0.0853
  11.250   1.0344   0.07406   0.06803  -0.0461   0.2005   0.0860
  11.500   1.0416   0.07616   0.07013  -0.0463   0.1972   0.0867
  11.750   1.0526   0.07784   0.07183  -0.0464   0.1942   0.0880
  12.000   1.0613   0.07982   0.07380  -0.0466   0.1891   0.0892
  12.250   1.0604   0.08303   0.07698  -0.0471   0.1817   0.0903
  12.750   1.0586   0.08950   0.08317  -0.0484   0.1348   0.0930
  13.000   1.0599   0.09248   0.08600  -0.0490   0.1170   0.0939
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