N-11 (n11-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-11 (n11-il) Reynolds number: 100,000 Max Cl/Cd: 56.23 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n11-il-100000-n5.txt Download as CSV file: xf-n11-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: N-11
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3645 0.09531 0.09053 -0.0409 1.0000 0.0498
-9.750 -0.3732 0.09293 0.08823 -0.0392 1.0000 0.0497
-9.500 -0.3849 0.09094 0.08633 -0.0369 1.0000 0.0495
-9.250 -0.3979 0.08907 0.08455 -0.0344 1.0000 0.0493
-9.000 -0.3930 0.08514 0.08063 -0.0372 0.9965 0.0490
-8.750 -0.3739 0.07993 0.07538 -0.0433 0.9898 0.0482
-8.500 -0.3546 0.07393 0.06932 -0.0512 0.9824 0.0474
-8.250 -0.3337 0.06681 0.06209 -0.0609 0.9744 0.0474
-8.000 -0.3143 0.05887 0.05392 -0.0702 0.9649 0.0481
-7.750 -0.2932 0.05139 0.04611 -0.0773 0.9569 0.0480
-7.500 -0.2699 0.04443 0.03867 -0.0829 0.9499 0.0478
-7.250 -0.2469 0.03882 0.03246 -0.0862 0.9424 0.0483
-7.000 -0.2196 0.03424 0.02706 -0.0889 0.9361 0.0497
-6.750 -0.1861 0.03114 0.02345 -0.0914 0.9325 0.0502
-6.500 -0.1627 0.02917 0.02116 -0.0914 0.9240 0.0507
-6.250 -0.1290 0.02733 0.01903 -0.0931 0.9196 0.0514
-6.000 -0.0985 0.02589 0.01734 -0.0939 0.9139 0.0523
-5.750 -0.0688 0.02482 0.01609 -0.0944 0.9072 0.0540
-5.500 -0.0337 0.02370 0.01472 -0.0959 0.9031 0.0564
-5.250 -0.0063 0.02271 0.01353 -0.0957 0.8952 0.0577
-5.000 0.0272 0.02167 0.01230 -0.0966 0.8901 0.0589
-4.750 0.0576 0.02085 0.01132 -0.0970 0.8835 0.0602
-4.500 0.0883 0.02004 0.01052 -0.0975 0.8770 0.0621
-4.250 0.1208 0.01939 0.00984 -0.0982 0.8714 0.0647
-4.000 0.1496 0.01889 0.00928 -0.0982 0.8633 0.0686
-3.750 0.1835 0.01830 0.00866 -0.0992 0.8582 0.0754
-3.500 0.2108 0.01790 0.00824 -0.0989 0.8489 0.0844
-3.250 0.2429 0.01729 0.00769 -0.0995 0.8418 0.1026
-3.000 0.2720 0.01683 0.00735 -0.0995 0.8319 0.1371
-2.750 0.3011 0.01649 0.00708 -0.0995 0.8212 0.1791
-2.500 0.3318 0.01605 0.00680 -0.0998 0.8109 0.2386
-2.250 0.3602 0.01550 0.00658 -0.0997 0.7989 0.3328
-2.000 0.3827 0.01461 0.00654 -0.0985 0.7860 0.5732
-1.750 0.4314 0.01367 0.00635 -0.1013 0.7747 1.0000
-1.500 0.4590 0.01371 0.00618 -0.1010 0.7639 1.0000
-1.250 0.4854 0.01377 0.00607 -0.1005 0.7523 1.0000
-1.000 0.5108 0.01386 0.00602 -0.0999 0.7399 1.0000
-0.750 0.5368 0.01394 0.00596 -0.0993 0.7277 1.0000
-0.500 0.5632 0.01402 0.00590 -0.0989 0.7157 1.0000
-0.250 0.5897 0.01409 0.00584 -0.0984 0.7035 1.0000
0.000 0.6156 0.01419 0.00582 -0.0979 0.6902 1.0000
0.250 0.6413 0.01429 0.00582 -0.0973 0.6767 1.0000
0.500 0.6672 0.01441 0.00584 -0.0968 0.6633 1.0000
0.750 0.6931 0.01454 0.00587 -0.0963 0.6496 1.0000
1.000 0.7189 0.01469 0.00591 -0.0958 0.6354 1.0000
1.250 0.7445 0.01485 0.00598 -0.0952 0.6210 1.0000
1.500 0.7699 0.01503 0.00607 -0.0947 0.6065 1.0000
1.750 0.7951 0.01524 0.00619 -0.0941 0.5917 1.0000
2.000 0.8200 0.01546 0.00635 -0.0935 0.5762 1.0000
2.250 0.8446 0.01570 0.00652 -0.0928 0.5601 1.0000
2.500 0.8687 0.01596 0.00670 -0.0921 0.5430 1.0000
2.750 0.8923 0.01624 0.00691 -0.0913 0.5246 1.0000
3.000 0.9155 0.01654 0.00711 -0.0904 0.5050 1.0000
3.250 0.9381 0.01685 0.00735 -0.0895 0.4850 1.0000
3.500 0.9608 0.01719 0.00763 -0.0887 0.4662 1.0000
3.750 0.9837 0.01754 0.00794 -0.0879 0.4496 1.0000
4.000 1.0066 0.01792 0.00826 -0.0871 0.4345 1.0000
4.250 1.0295 0.01831 0.00863 -0.0863 0.4210 1.0000
4.500 1.0522 0.01872 0.00901 -0.0856 0.4088 1.0000
4.750 1.0748 0.01916 0.00941 -0.0848 0.3972 1.0000
5.000 1.0973 0.01960 0.00987 -0.0841 0.3859 1.0000
5.250 1.1194 0.02007 0.01035 -0.0833 0.3749 1.0000
5.500 1.1410 0.02057 0.01081 -0.0825 0.3644 1.0000
5.750 1.1625 0.02107 0.01134 -0.0816 0.3536 1.0000
6.000 1.1839 0.02158 0.01191 -0.0808 0.3438 1.0000
6.500 1.2255 0.02267 0.01308 -0.0790 0.3246 1.0000
6.750 1.2460 0.02325 0.01369 -0.0781 0.3160 1.0000
7.000 1.2658 0.02381 0.01437 -0.0770 0.3068 1.0000
7.250 1.2854 0.02440 0.01504 -0.0760 0.2982 1.0000
7.500 1.3034 0.02500 0.01570 -0.0747 0.2886 1.0000
7.750 1.3187 0.02557 0.01639 -0.0731 0.2760 1.0000
8.000 1.3320 0.02617 0.01708 -0.0712 0.2620 1.0000
8.250 1.3435 0.02679 0.01780 -0.0690 0.2481 1.0000
8.500 1.3547 0.02747 0.01856 -0.0668 0.2351 1.0000
8.750 1.3650 0.02824 0.01940 -0.0646 0.2213 1.0000
9.000 1.3744 0.02912 0.02033 -0.0625 0.2072 1.0000
9.250 1.3837 0.03009 0.02137 -0.0605 0.1950 1.0000
9.500 1.3915 0.03121 0.02253 -0.0584 0.1830 1.0000
9.750 1.3967 0.03254 0.02390 -0.0563 0.1684 1.0000
10.000 1.4008 0.03406 0.02544 -0.0543 0.1529 1.0000
10.250 1.4053 0.03566 0.02710 -0.0525 0.1368 1.0000
10.500 1.4064 0.03760 0.02904 -0.0507 0.1137 1.0000
10.750 1.3998 0.04031 0.03159 -0.0487 0.0921 1.0000
11.000 1.3914 0.04339 0.03459 -0.0470 0.0779 1.0000
11.250 1.3851 0.04645 0.03769 -0.0457 0.0646 1.0000
11.500 1.3783 0.04973 0.04103 -0.0447 0.0493 1.0000
11.750 1.3671 0.05364 0.04495 -0.0441 0.0394 1.0000
12.000 1.3557 0.05781 0.04916 -0.0438 0.0345 1.0000
12.250 1.3440 0.06225 0.05370 -0.0440 0.0318 1.0000
12.500 1.3327 0.06690 0.05849 -0.0445 0.0302 1.0000
12.750 1.3200 0.07196 0.06373 -0.0454 0.0290 1.0000
13.000 1.3061 0.07743 0.06937 -0.0467 0.0282 1.0000
13.250 1.2913 0.08330 0.07540 -0.0483 0.0277 1.0000
13.500 1.2760 0.08946 0.08172 -0.0502 0.0272 1.0000
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Polar data table (+)
Polar graphs
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