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
|
Polar data table (+)
Polar graphs
<< Back to LIEBECK L1003 AIRFOIL (l1003-il)