LIEBECK L1003 AIRFOIL (l1003-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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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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Polar data table (+)
Polar graphs
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