N-11 (n11-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-11 (n11-il) Reynolds number: 50,000 Max Cl/Cd: 38.09 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n11-il-50000-n5.txt Download as CSV file: xf-n11-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3298 0.11087 0.10394 -0.0350 1.0000 0.1291
-10.000 -0.3469 0.10971 0.10294 -0.0356 1.0000 0.1302
-9.750 -0.3635 0.10831 0.10169 -0.0351 1.0000 0.1305
-9.500 -0.3333 0.10266 0.09599 -0.0325 1.0000 0.1349
-9.250 -0.3374 0.10042 0.09384 -0.0311 1.0000 0.1365
-8.750 -0.3894 0.09215 0.08580 -0.0349 1.0000 0.0851
-8.500 -0.3884 0.08957 0.08327 -0.0322 1.0000 0.0830
-8.250 -0.3943 0.08679 0.08056 -0.0313 1.0000 0.0810
-8.000 -0.4012 0.08363 0.07744 -0.0315 1.0000 0.0789
-7.500 -0.4126 0.07161 0.06516 -0.0412 1.0000 0.0720
-7.250 -0.3975 0.06870 0.06227 -0.0422 0.9967 0.0737
-7.000 -0.3709 0.06502 0.05846 -0.0463 0.9902 0.0755
-6.750 -0.3399 0.05798 0.05098 -0.0545 0.9832 0.0742
-6.500 -0.3071 0.05094 0.04320 -0.0617 0.9762 0.0727
-6.250 -0.2756 0.04680 0.03856 -0.0655 0.9698 0.0728
-6.000 -0.2439 0.04448 0.03609 -0.0681 0.9634 0.0747
-5.750 -0.2127 0.04226 0.03359 -0.0705 0.9564 0.0774
-5.500 -0.1775 0.03946 0.03029 -0.0734 0.9501 0.0792
-5.250 -0.1432 0.03690 0.02719 -0.0757 0.9436 0.0801
-5.000 -0.1085 0.03477 0.02457 -0.0776 0.9367 0.0815
-4.750 -0.0703 0.03295 0.02225 -0.0799 0.9313 0.0836
-4.500 -0.0393 0.03166 0.02061 -0.0807 0.9229 0.0868
-4.250 -0.0011 0.03071 0.01959 -0.0830 0.9175 0.0924
-4.000 0.0280 0.02985 0.01850 -0.0833 0.9083 0.0973
-3.750 0.0671 0.02885 0.01732 -0.0852 0.9029 0.1030
-3.500 0.0960 0.02824 0.01662 -0.0854 0.8936 0.1107
-3.250 0.1365 0.02749 0.01579 -0.0876 0.8882 0.1276
-3.000 0.1655 0.02700 0.01539 -0.0880 0.8786 0.1560
-2.750 0.2064 0.02627 0.01485 -0.0905 0.8733 0.2165
-2.500 0.2338 0.02568 0.01471 -0.0909 0.8633 0.3044
-2.250 0.2676 0.02442 0.01439 -0.0920 0.8575 0.4866
-2.000 0.3010 0.02322 0.01415 -0.0915 0.8480 1.0000
-1.750 0.3340 0.02326 0.01380 -0.0921 0.8376 1.0000
-1.500 0.3750 0.02302 0.01322 -0.0938 0.8287 1.0000
-1.250 0.4052 0.02297 0.01292 -0.0938 0.8152 1.0000
-1.000 0.4350 0.02293 0.01266 -0.0936 0.8018 1.0000
-0.750 0.4643 0.02294 0.01248 -0.0935 0.7892 1.0000
-0.500 0.4954 0.02294 0.01230 -0.0937 0.7784 1.0000
-0.250 0.5262 0.02295 0.01216 -0.0938 0.7676 1.0000
0.000 0.5512 0.02312 0.01223 -0.0931 0.7546 1.0000
0.250 0.5774 0.02326 0.01226 -0.0925 0.7419 1.0000
0.500 0.6049 0.02334 0.01225 -0.0921 0.7297 1.0000
0.750 0.6345 0.02334 0.01215 -0.0920 0.7183 1.0000
1.000 0.6613 0.02342 0.01216 -0.0915 0.7054 1.0000
1.250 0.6866 0.02356 0.01224 -0.0907 0.6914 1.0000
1.500 0.7123 0.02368 0.01233 -0.0901 0.6776 1.0000
1.750 0.7384 0.02380 0.01240 -0.0895 0.6636 1.0000
2.000 0.7648 0.02391 0.01246 -0.0889 0.6493 1.0000
2.250 0.7913 0.02404 0.01257 -0.0883 0.6348 1.0000
2.500 0.8176 0.02420 0.01268 -0.0877 0.6199 1.0000
2.750 0.8436 0.02439 0.01284 -0.0871 0.6047 1.0000
3.000 0.8692 0.02463 0.01305 -0.0864 0.5891 1.0000
3.250 0.8944 0.02492 0.01331 -0.0858 0.5735 1.0000
3.500 0.9191 0.02524 0.01362 -0.0851 0.5576 1.0000
3.750 0.9434 0.02561 0.01398 -0.0844 0.5418 1.0000
4.000 0.9670 0.02600 0.01436 -0.0835 0.5258 1.0000
4.250 0.9900 0.02641 0.01475 -0.0827 0.5097 1.0000
4.500 1.0126 0.02686 0.01522 -0.0817 0.4941 1.0000
4.750 1.0348 0.02735 0.01572 -0.0808 0.4792 1.0000
5.000 1.0569 0.02787 0.01626 -0.0800 0.4653 1.0000
5.250 1.0793 0.02842 0.01683 -0.0791 0.4524 1.0000
5.500 1.1026 0.02895 0.01740 -0.0785 0.4406 1.0000
5.750 1.1238 0.02960 0.01814 -0.0776 0.4287 1.0000
6.000 1.1443 0.03033 0.01897 -0.0767 0.4174 1.0000
6.250 1.1664 0.03102 0.01975 -0.0760 0.4071 1.0000
6.500 1.1896 0.03165 0.02043 -0.0754 0.3972 1.0000
6.750 1.2080 0.03254 0.02147 -0.0743 0.3864 1.0000
7.000 1.2292 0.03333 0.02236 -0.0735 0.3767 1.0000
7.250 1.2513 0.03410 0.02325 -0.0728 0.3673 1.0000
7.500 1.2675 0.03511 0.02443 -0.0715 0.3566 1.0000
7.750 1.2859 0.03594 0.02535 -0.0703 0.3458 1.0000
8.000 1.3064 0.03664 0.02608 -0.0693 0.3347 1.0000
8.250 1.3160 0.03780 0.02746 -0.0672 0.3232 1.0000
8.500 1.3289 0.03883 0.02867 -0.0655 0.3124 1.0000
8.750 1.3467 0.03963 0.02952 -0.0643 0.3023 1.0000
9.000 1.3526 0.04103 0.03120 -0.0619 0.2926 1.0000
9.250 1.3632 0.04216 0.03249 -0.0599 0.2836 1.0000
9.500 1.3704 0.04320 0.03367 -0.0576 0.2738 1.0000
9.750 1.3673 0.04480 0.03551 -0.0544 0.2638 1.0000
10.000 1.3666 0.04614 0.03697 -0.0516 0.2534 1.0000
10.250 1.3653 0.04745 0.03838 -0.0491 0.2425 1.0000
10.500 1.3559 0.04979 0.04095 -0.0466 0.2322 1.0000
10.750 1.3490 0.05216 0.04349 -0.0447 0.2223 1.0000
11.000 1.3448 0.05438 0.04582 -0.0432 0.2128 1.0000
11.250 1.3377 0.05727 0.04890 -0.0421 0.2035 1.0000
11.500 1.3295 0.06054 0.05235 -0.0414 0.1945 1.0000
11.750 1.3230 0.06355 0.05543 -0.0408 0.1848 1.0000
12.000 1.3121 0.06745 0.05948 -0.0408 0.1749 1.0000
12.250 1.2990 0.07197 0.06414 -0.0413 0.1651 1.0000
12.500 1.2875 0.07632 0.06856 -0.0419 0.1548 1.0000
12.750 1.2738 0.08130 0.07363 -0.0430 0.1444 1.0000
13.000 1.2554 0.08762 0.08017 -0.0449 0.1351 1.0000
13.250 1.2394 0.09364 0.08631 -0.0468 0.1254 1.0000
13.500 1.2258 0.09941 0.09215 -0.0488 0.1158 1.0000
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Polar data table (+)
Polar graphs
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