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LIEBECK L1003 AIRFOIL (l1003-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: LIEBECK L1003 AIRFOIL (l1003-il)
Reynolds number: 1,000,000
Max Cl/Cd: 68.81 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-l1003-il-1000000-n5.txt
Download as CSV file: xf-l1003-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2191   0.08409   0.08011   0.0055   0.3693   0.0330
  -6.250  -0.3901   0.01733   0.01104  -0.0356   0.3705   0.0394
  -6.000  -0.3625   0.01653   0.01010  -0.0356   0.3698   0.0397
  -5.750  -0.3344   0.01590   0.00937  -0.0355   0.3693   0.0399
  -5.500  -0.3059   0.01537   0.00876  -0.0354   0.3691   0.0401
  -5.250  -0.2772   0.01491   0.00823  -0.0353   0.3689   0.0403
  -5.000  -0.2483   0.01451   0.00776  -0.0352   0.3687   0.0405
  -4.750  -0.2193   0.01416   0.00735  -0.0351   0.3684   0.0407
  -4.500  -0.1901   0.01384   0.00698  -0.0350   0.3682   0.0408
  -4.250  -0.1608   0.01358   0.00669  -0.0349   0.3679   0.0412
  -4.000  -0.1314   0.01338   0.00647  -0.0348   0.3676   0.0416
  -3.750  -0.1018   0.01320   0.00627  -0.0347   0.3673   0.0419
  -3.500  -0.0722   0.01302   0.00609  -0.0347   0.3669   0.0423
  -3.250  -0.0426   0.01286   0.00591  -0.0346   0.3663   0.0427
  -3.000  -0.0130   0.01269   0.00573  -0.0345   0.3656   0.0431
  -2.750   0.0166   0.01253   0.00555  -0.0345   0.3650   0.0436
  -2.500   0.0462   0.01236   0.00536  -0.0344   0.3646   0.0441
  -2.250   0.0758   0.01220   0.00518  -0.0344   0.3642   0.0445
  -2.000   0.1054   0.01204   0.00500  -0.0344   0.3638   0.0450
  -1.750   0.1352   0.01195   0.00491  -0.0344   0.3634   0.0456
  -1.500   0.1652   0.01192   0.00489  -0.0344   0.3629   0.0462
  -1.250   0.1952   0.01189   0.00488  -0.0344   0.3620   0.0470
  -1.000   0.2251   0.01185   0.00483  -0.0344   0.3609   0.0478
  -0.750   0.2549   0.01176   0.00472  -0.0344   0.3599   0.0487
  -0.500   0.2845   0.01163   0.00458  -0.0344   0.3591   0.0497
  -0.250   0.3146   0.01169   0.00466  -0.0345   0.3585   0.0503
   0.000   0.3447   0.01175   0.00473  -0.0345   0.3580   0.0509
   0.250   0.3747   0.01178   0.00477  -0.0346   0.3572   0.0516
   0.500   0.4046   0.01178   0.00475  -0.0347   0.3557   0.0526
   0.750   0.4342   0.01169   0.00462  -0.0347   0.3539   0.0538
   1.000   0.4641   0.01163   0.00458  -0.0348   0.3530   0.0545
   1.250   0.4941   0.01166   0.00463  -0.0348   0.3518   0.0550
   1.500   0.5241   0.01169   0.00469  -0.0349   0.3506   0.0555
   1.750   0.5541   0.01171   0.00472  -0.0350   0.3492   0.0561
   2.000   0.5839   0.01171   0.00471  -0.0351   0.3477   0.0570
   2.250   0.6136   0.01167   0.00466  -0.0352   0.3462   0.0580
   2.500   0.6432   0.01164   0.00459  -0.0353   0.3444   0.0589
   2.750   0.6730   0.01167   0.00463  -0.0355   0.3421   0.0595
   3.000   0.7027   0.01175   0.00472  -0.0356   0.3395   0.0600
   3.250   0.7325   0.01177   0.00476  -0.0358   0.3379   0.0605
   3.500   0.7621   0.01179   0.00479  -0.0359   0.3355   0.0612
   3.750   0.7916   0.01182   0.00481  -0.0361   0.3310   0.0619
   4.000   0.8209   0.01193   0.00489  -0.0363   0.3241   0.0628
   4.250   0.8430   0.01511   0.00772  -0.0388   0.2232   0.0636
   4.500   0.8695   0.01612   0.00871  -0.0398   0.2085   0.0643
   4.750   0.8963   0.01693   0.00956  -0.0406   0.2012   0.0647
   5.000   0.9219   0.01815   0.01080  -0.0417   0.1944   0.0653
   5.250   0.9472   0.01940   0.01212  -0.0429   0.1898   0.0658
   5.500   0.9545   0.02533   0.01826  -0.0494   0.1837   0.0661
   5.750   0.9132   0.03303   0.02617  -0.0540   0.1852   0.0659
   6.000   0.8720   0.03695   0.03016  -0.0506   0.1875   0.0657
   6.250   0.8500   0.04050   0.03375  -0.0489   0.1864   0.0658
   6.500   0.8245   0.04475   0.03801  -0.0478   0.1822   0.0658
   6.750   0.8187   0.04749   0.04076  -0.0472   0.1793   0.0659
   7.000   0.8128   0.05037   0.04365  -0.0467   0.1750   0.0661
   7.250   0.7825   0.05568   0.04882  -0.0466   0.1470   0.0661
   7.500   0.7772   0.05874   0.05183  -0.0464   0.1337   0.0663
   7.750   0.7675   0.06233   0.05533  -0.0465   0.1129   0.0664
   8.000   0.7766   0.06403   0.05702  -0.0463   0.1090   0.0667
   8.250   0.7867   0.06565   0.05863  -0.0462   0.1060   0.0670
   8.500   0.7983   0.06714   0.06012  -0.0461   0.1031   0.0674
   8.750   0.8106   0.06858   0.06156  -0.0460   0.1017   0.0677
   9.000   0.8228   0.07006   0.06304  -0.0459   0.1000   0.0681
   9.250   0.8342   0.07165   0.06462  -0.0459   0.0978   0.0685
   9.500   0.8451   0.07331   0.06628  -0.0459   0.0957   0.0689
   9.750   0.8560   0.07505   0.06804  -0.0460   0.0949   0.0691
  10.000   0.8680   0.07661   0.06961  -0.0460   0.0933   0.0697
  10.250   0.8805   0.07812   0.07113  -0.0460   0.0912   0.0699
  10.500   0.8927   0.07968   0.07267  -0.0461   0.0879   0.0704
  10.750   0.9060   0.08113   0.07413  -0.0462   0.0856   0.0707
  11.000   0.9084   0.08384   0.07665  -0.0466   0.0493   0.0711
  11.250   0.9206   0.08547   0.07827  -0.0467   0.0464   0.0715
  11.500   0.9330   0.08707   0.07988  -0.0469   0.0449   0.0719
  11.750   0.9463   0.08859   0.08142  -0.0471   0.0445   0.0724
  12.000   0.9588   0.09022   0.08305  -0.0473   0.0434   0.0730
  12.250   0.9716   0.09183   0.08467  -0.0475   0.0428   0.0734
  12.500   0.9844   0.09344   0.08631  -0.0477   0.0426   0.0741
  12.750   0.9961   0.09522   0.08811  -0.0480   0.0422   0.0745
  13.000   1.0068   0.09716   0.09008  -0.0484   0.0418   0.0749
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