LIEBECK L1003 AIRFOIL (l1003-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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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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Polar data table (+)
Polar graphs
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