N-11 (n11-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-11 (n11-il) Reynolds number: 50,000 Max Cl/Cd: 27.1 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n11-il-50000.txt Download as CSV file: xf-n11-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3292 0.10967 0.10291 -0.0281 1.0000 0.2139
-9.500 -0.3257 0.10614 0.09945 -0.0271 1.0000 0.2182
-9.250 -0.3221 0.10358 0.09695 -0.0255 1.0000 0.2271
-9.000 -0.3540 0.10435 0.09795 -0.0235 1.0000 0.2305
-8.750 -0.3306 0.09927 0.09285 -0.0218 1.0000 0.2408
-8.500 -0.3596 0.09950 0.09327 -0.0188 1.0000 0.2456
-8.250 -0.3541 0.09612 0.08995 -0.0165 1.0000 0.2529
-8.000 -0.3724 0.09533 0.08930 -0.0137 1.0000 0.2604
-7.750 -0.3899 0.09378 0.08790 -0.0120 1.0000 0.2654
-7.500 -0.3893 0.09148 0.08565 -0.0092 1.0000 0.2759
-7.000 -0.4142 0.08830 0.08266 -0.0071 1.0000 0.2946
-6.750 -0.4066 0.08495 0.07934 -0.0032 1.0000 0.3033
-6.500 -0.4142 0.08284 0.07731 -0.0022 1.0000 0.3156
-6.250 -0.4188 0.08071 0.07524 -0.0012 1.0000 0.3303
-6.000 -0.4197 0.07840 0.07298 0.0006 1.0000 0.3465
-5.750 -0.4180 0.07603 0.07067 0.0035 1.0000 0.3645
-5.500 -0.4213 0.07432 0.06900 0.0044 1.0000 0.3928
-5.250 -0.4170 0.07176 0.06652 0.0100 1.0000 0.4150
-5.000 -0.4171 0.06974 0.06457 0.0142 1.0000 0.4472
-4.500 -0.2695 0.05079 0.04341 -0.0428 1.0000 0.1993
-4.250 -0.2416 0.04675 0.03909 -0.0449 1.0000 0.1791
-4.000 -0.2056 0.04326 0.03474 -0.0487 1.0000 0.1667
-3.750 -0.1800 0.04125 0.03240 -0.0498 1.0000 0.1661
-3.500 -0.1541 0.03946 0.03028 -0.0508 1.0000 0.1649
-3.250 -0.1277 0.03794 0.02837 -0.0516 1.0000 0.1643
-3.000 -0.1015 0.03676 0.02679 -0.0523 1.0000 0.1654
-2.750 -0.0765 0.03585 0.02560 -0.0528 1.0000 0.1694
-2.500 -0.0544 0.03538 0.02507 -0.0529 1.0000 0.1779
-2.250 -0.0132 0.03487 0.02432 -0.0561 0.9949 0.1908
-2.000 0.0448 0.03436 0.02368 -0.0617 0.9839 0.2227
-1.750 0.1040 0.03327 0.02300 -0.0673 0.9718 0.3365
-1.500 0.1453 0.03061 0.02247 -0.0684 0.9583 1.0000
-1.250 0.1994 0.03159 0.02271 -0.0737 0.9419 1.0000
-1.000 0.2407 0.03233 0.02306 -0.0768 0.9252 1.0000
-0.750 0.2804 0.03304 0.02348 -0.0795 0.9094 1.0000
-0.500 0.3187 0.03371 0.02391 -0.0819 0.8939 1.0000
-0.250 0.3560 0.03434 0.02434 -0.0841 0.8782 1.0000
0.000 0.3927 0.03493 0.02478 -0.0860 0.8624 1.0000
0.250 0.4289 0.03549 0.02520 -0.0877 0.8465 1.0000
0.500 0.4648 0.03598 0.02559 -0.0892 0.8301 1.0000
0.750 0.5004 0.03644 0.02596 -0.0905 0.8137 1.0000
1.000 0.5358 0.03683 0.02629 -0.0916 0.7972 1.0000
1.250 0.5714 0.03713 0.02654 -0.0926 0.7805 1.0000
1.500 0.6066 0.03736 0.02675 -0.0933 0.7641 1.0000
1.750 0.6420 0.03749 0.02686 -0.0939 0.7479 1.0000
2.000 0.6780 0.03750 0.02687 -0.0944 0.7320 1.0000
2.250 0.7124 0.03752 0.02689 -0.0946 0.7164 1.0000
2.500 0.7450 0.03754 0.02693 -0.0945 0.7010 1.0000
2.750 0.7764 0.03759 0.02700 -0.0942 0.6857 1.0000
3.000 0.8062 0.03774 0.02717 -0.0938 0.6708 1.0000
3.250 0.8355 0.03787 0.02733 -0.0932 0.6561 1.0000
3.500 0.8643 0.03804 0.02754 -0.0926 0.6416 1.0000
3.750 0.8938 0.03809 0.02763 -0.0919 0.6273 1.0000
4.000 0.9242 0.03807 0.02763 -0.0913 0.6133 1.0000
4.250 0.9569 0.03788 0.02750 -0.0908 0.5998 1.0000
4.500 0.9992 0.03704 0.02667 -0.0912 0.5880 1.0000
4.750 1.0221 0.03771 0.02740 -0.0902 0.5740 1.0000
5.000 1.0389 0.03888 0.02866 -0.0887 0.5600 1.0000
5.250 1.0530 0.04032 0.03021 -0.0872 0.5465 1.0000
5.500 1.0687 0.04169 0.03168 -0.0858 0.5336 1.0000
5.750 1.0931 0.04241 0.03249 -0.0850 0.5217 1.0000
6.000 1.1345 0.04193 0.03208 -0.0855 0.5111 1.0000
6.250 1.1311 0.04486 0.03519 -0.0828 0.4984 1.0000
6.500 1.1277 0.04791 0.03837 -0.0803 0.4864 1.0000
6.750 1.1475 0.04911 0.03969 -0.0793 0.4755 1.0000
7.000 1.1925 0.04838 0.03908 -0.0798 0.4651 1.0000
7.250 1.0890 0.06036 0.05111 -0.0731 0.4545 1.0000
7.500 1.0010 0.07484 0.06545 -0.0738 0.4448 1.0000
7.750 0.9871 0.08059 0.07126 -0.0741 0.4369 1.0000
8.000 1.2451 0.05444 0.04565 -0.0731 0.4177 1.0000
8.250 1.2789 0.05370 0.04503 -0.0722 0.4027 1.0000
8.500 1.1269 0.07203 0.06331 -0.0665 0.4032 1.0000
8.750 1.1696 0.06920 0.06067 -0.0641 0.3888 1.0000
9.000 1.0160 0.09535 0.08646 -0.0708 0.3880 1.0000
9.250 0.9594 0.10673 0.09776 -0.0739 0.3851 1.0000
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Polar data table (+)
Polar graphs
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