N-11 (n11-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-11 (n11-il) Reynolds number: 200,000 Max Cl/Cd: 72.03 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n11-il-200000-n5.txt Download as CSV file: xf-n11-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3435 0.09521 0.09167 -0.0387 1.0000 0.0284
-10.250 -0.3501 0.09242 0.08895 -0.0383 1.0000 0.0290
-10.000 -0.3605 0.08971 0.08630 -0.0373 1.0000 0.0293
-9.750 -0.3565 0.08482 0.08143 -0.0418 0.9960 0.0295
-9.500 -0.3477 0.07882 0.07543 -0.0490 0.9884 0.0296
-9.250 -0.3351 0.07143 0.06802 -0.0594 0.9791 0.0299
-9.000 -0.3225 0.05974 0.05621 -0.0757 0.9681 0.0310
-8.750 -0.3242 0.03846 0.03401 -0.0944 0.9538 0.0317
-8.500 -0.3046 0.03202 0.02684 -0.0985 0.9478 0.0326
-8.250 -0.2836 0.03002 0.02467 -0.0988 0.9391 0.0334
-8.000 -0.2556 0.02799 0.02237 -0.1003 0.9341 0.0343
-7.750 -0.2321 0.02592 0.01996 -0.1005 0.9261 0.0349
-7.500 -0.2046 0.02400 0.01771 -0.1012 0.9199 0.0355
-7.250 -0.1776 0.02247 0.01588 -0.1015 0.9131 0.0362
-7.000 -0.1498 0.02125 0.01440 -0.1017 0.9061 0.0374
-6.750 -0.1202 0.02005 0.01292 -0.1022 0.9002 0.0383
-6.500 -0.0924 0.01898 0.01161 -0.1022 0.8926 0.0387
-6.250 -0.0615 0.01800 0.01043 -0.1028 0.8870 0.0392
-6.000 -0.0336 0.01722 0.00949 -0.1027 0.8790 0.0397
-5.500 0.0249 0.01579 0.00782 -0.1031 0.8648 0.0407
-5.250 0.0544 0.01505 0.00703 -0.1034 0.8583 0.0422
-5.000 0.0819 0.01459 0.00654 -0.1032 0.8499 0.0436
-4.750 0.1109 0.01416 0.00603 -0.1033 0.8421 0.0447
-4.500 0.1387 0.01378 0.00558 -0.1031 0.8323 0.0458
-4.250 0.1665 0.01346 0.00518 -0.1029 0.8223 0.0470
-4.000 0.1947 0.01319 0.00480 -0.1027 0.8125 0.0485
-3.750 0.2218 0.01296 0.00450 -0.1024 0.8015 0.0502
-3.500 0.2489 0.01272 0.00423 -0.1021 0.7911 0.0537
-3.250 0.2764 0.01254 0.00400 -0.1018 0.7810 0.0595
-3.000 0.3030 0.01231 0.00383 -0.1015 0.7693 0.0776
-2.750 0.3294 0.01208 0.00369 -0.1011 0.7569 0.1106
-2.500 0.3560 0.01190 0.00358 -0.1008 0.7442 0.1455
-2.250 0.3827 0.01175 0.00350 -0.1005 0.7325 0.1832
-2.000 0.4094 0.01161 0.00343 -0.1002 0.7210 0.2187
-1.750 0.4357 0.01144 0.00337 -0.0999 0.7084 0.2642
-1.500 0.4616 0.01119 0.00333 -0.0996 0.6954 0.3443
-1.250 0.4833 0.01047 0.00338 -0.0985 0.6826 0.5904
-1.000 0.5299 0.00968 0.00339 -0.1015 0.6693 1.0000
-0.750 0.5555 0.00979 0.00334 -0.1009 0.6564 1.0000
-0.500 0.5810 0.00991 0.00332 -0.1004 0.6429 1.0000
-0.250 0.6065 0.01004 0.00332 -0.0998 0.6291 1.0000
0.000 0.6319 0.01019 0.00334 -0.0993 0.6152 1.0000
0.250 0.6574 0.01034 0.00338 -0.0988 0.6018 1.0000
0.500 0.6829 0.01050 0.00344 -0.0983 0.5890 1.0000
0.750 0.7084 0.01067 0.00351 -0.0978 0.5760 1.0000
1.000 0.7335 0.01085 0.00360 -0.0972 0.5613 1.0000
1.250 0.7582 0.01105 0.00370 -0.0966 0.5442 1.0000
1.500 0.7827 0.01127 0.00380 -0.0960 0.5261 1.0000
1.750 0.8070 0.01149 0.00393 -0.0954 0.5079 1.0000
2.000 0.8309 0.01174 0.00407 -0.0947 0.4887 1.0000
2.250 0.8548 0.01199 0.00423 -0.0940 0.4684 1.0000
2.500 0.8785 0.01226 0.00440 -0.0933 0.4478 1.0000
2.750 0.9020 0.01255 0.00460 -0.0926 0.4292 1.0000
3.000 0.9254 0.01285 0.00482 -0.0919 0.4123 1.0000
3.250 0.9487 0.01317 0.00505 -0.0911 0.3965 1.0000
3.500 0.9717 0.01350 0.00532 -0.0904 0.3818 1.0000
3.750 0.9947 0.01385 0.00560 -0.0897 0.3679 1.0000
4.000 1.0177 0.01420 0.00590 -0.0890 0.3554 1.0000
4.250 1.0407 0.01455 0.00622 -0.0883 0.3450 1.0000
4.500 1.0635 0.01492 0.00655 -0.0876 0.3359 1.0000
4.750 1.0872 0.01524 0.00689 -0.0871 0.3283 1.0000
5.000 1.1100 0.01561 0.00726 -0.0864 0.3211 1.0000
5.250 1.1332 0.01595 0.00763 -0.0858 0.3137 1.0000
5.500 1.1555 0.01633 0.00801 -0.0851 0.3054 1.0000
5.750 1.1782 0.01668 0.00840 -0.0845 0.2975 1.0000
6.000 1.2000 0.01708 0.00882 -0.0837 0.2894 1.0000
6.250 1.2217 0.01744 0.00923 -0.0829 0.2787 1.0000
6.500 1.2423 0.01784 0.00964 -0.0819 0.2661 1.0000
6.750 1.2621 0.01826 0.01007 -0.0809 0.2525 1.0000
7.000 1.2817 0.01870 0.01053 -0.0798 0.2397 1.0000
7.250 1.3005 0.01917 0.01101 -0.0786 0.2263 1.0000
7.500 1.3174 0.01970 0.01153 -0.0771 0.2100 1.0000
7.750 1.3309 0.02035 0.01211 -0.0752 0.1912 1.0000
8.000 1.3434 0.02112 0.01281 -0.0731 0.1746 1.0000
8.250 1.3557 0.02194 0.01361 -0.0711 0.1595 1.0000
8.500 1.3683 0.02277 0.01443 -0.0693 0.1450 1.0000
8.750 1.3801 0.02367 0.01531 -0.0674 0.1255 1.0000
9.000 1.3822 0.02525 0.01663 -0.0646 0.0909 1.0000
9.250 1.3867 0.02673 0.01803 -0.0621 0.0757 1.0000
9.500 1.3934 0.02810 0.01941 -0.0600 0.0620 1.0000
10.000 1.3881 0.03248 0.02355 -0.0548 0.0229 1.0000
10.250 1.3917 0.03432 0.02547 -0.0531 0.0206 1.0000
10.500 1.3954 0.03620 0.02748 -0.0516 0.0192 1.0000
10.750 1.3974 0.03832 0.02972 -0.0502 0.0181 1.0000
11.000 1.3970 0.04074 0.03227 -0.0489 0.0171 1.0000
11.250 1.3970 0.04323 0.03490 -0.0479 0.0164 1.0000
11.500 1.3978 0.04573 0.03755 -0.0471 0.0159 1.0000
11.750 1.3967 0.04851 0.04049 -0.0464 0.0154 1.0000
12.000 1.3939 0.05160 0.04376 -0.0460 0.0150 1.0000
12.250 1.3899 0.05498 0.04729 -0.0458 0.0147 1.0000
12.500 1.3844 0.05867 0.05113 -0.0459 0.0144 1.0000
12.750 1.3776 0.06269 0.05531 -0.0462 0.0142 1.0000
13.000 1.3696 0.06704 0.05981 -0.0468 0.0140 1.0000
13.250 1.3604 0.07169 0.06460 -0.0477 0.0138 1.0000
13.500 1.3506 0.07657 0.06963 -0.0487 0.0136 1.0000
13.750 1.3398 0.08175 0.07494 -0.0500 0.0134 1.0000
14.000 1.3283 0.08712 0.08045 -0.0515 0.0133 1.0000
14.250 1.3167 0.09258 0.08603 -0.0530 0.0131 1.0000
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Polar data table (+)
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