N-11 (n11-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-11 (n11-il) Reynolds number: 500,000 Max Cl/Cd: 100.9 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n11-il-500000.txt Download as CSV file: xf-n11-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3586 0.09415 0.09194 -0.0393 1.0000 0.0305
-10.250 -0.3704 0.09137 0.08921 -0.0384 1.0000 0.0306
-10.000 -0.3759 0.08508 0.08296 -0.0421 0.9980 0.0310
-9.750 -0.3567 0.08266 0.08053 -0.0440 0.9959 0.0315
-9.500 -0.3358 0.08001 0.07787 -0.0474 0.9937 0.0322
-9.250 -0.3183 0.07634 0.07420 -0.0523 0.9886 0.0332
-8.750 -0.2743 0.05155 0.04916 -0.0910 0.9735 0.0382
-8.500 -0.2458 0.04981 0.04739 -0.0939 0.9716 0.0390
-8.250 -0.2221 0.04764 0.04517 -0.0962 0.9656 0.0401
-8.000 -0.2037 0.03526 0.03209 -0.1065 0.9573 0.0466
-7.750 -0.1983 0.02400 0.01959 -0.1074 0.9451 0.0380
-7.500 -0.1728 0.02218 0.01749 -0.1074 0.9384 0.0377
-7.250 -0.1478 0.02063 0.01569 -0.1071 0.9306 0.0376
-7.000 -0.1213 0.01941 0.01427 -0.1069 0.9234 0.0374
-6.750 -0.0965 0.01756 0.01218 -0.1065 0.9151 0.0372
-6.500 -0.0708 0.01622 0.01060 -0.1061 0.9066 0.0375
-6.250 -0.0450 0.01439 0.00854 -0.1059 0.8986 0.0381
-6.000 -0.0189 0.01342 0.00745 -0.1054 0.8887 0.0386
-5.750 0.0082 0.01267 0.00659 -0.1051 0.8793 0.0390
-5.500 0.0351 0.01207 0.00589 -0.1047 0.8691 0.0395
-5.250 0.0618 0.01157 0.00533 -0.1043 0.8589 0.0401
-5.000 0.0890 0.01116 0.00483 -0.1040 0.8499 0.0407
-4.750 0.1160 0.01082 0.00443 -0.1036 0.8402 0.0418
-4.500 0.1430 0.01053 0.00407 -0.1033 0.8309 0.0429
-4.250 0.1703 0.01026 0.00371 -0.1029 0.8220 0.0438
-4.000 0.1972 0.01001 0.00341 -0.1026 0.8122 0.0446
-3.750 0.2245 0.00983 0.00315 -0.1023 0.8028 0.0454
-3.500 0.2513 0.00953 0.00281 -0.1019 0.7927 0.0475
-3.250 0.2786 0.00935 0.00261 -0.1016 0.7827 0.0504
-3.000 0.3061 0.00924 0.00244 -0.1014 0.7736 0.0544
-2.750 0.3332 0.00900 0.00230 -0.1011 0.7631 0.0742
-2.500 0.3599 0.00871 0.00221 -0.1009 0.7527 0.1375
-2.250 0.3870 0.00856 0.00215 -0.1007 0.7420 0.1843
-2.000 0.4140 0.00840 0.00211 -0.1005 0.7302 0.2291
-1.750 0.4407 0.00821 0.00206 -0.1003 0.7180 0.2872
-1.500 0.4664 0.00784 0.00205 -0.1000 0.7054 0.4221
-1.250 0.4885 0.00715 0.00210 -0.0990 0.6923 0.6740
-1.000 0.5259 0.00658 0.00218 -0.1003 0.6779 0.9835
-0.750 0.5643 0.00667 0.00215 -0.1026 0.6626 1.0000
-0.500 0.5894 0.00679 0.00214 -0.1020 0.6480 1.0000
-0.250 0.6145 0.00692 0.00216 -0.1014 0.6329 1.0000
0.000 0.6396 0.00706 0.00219 -0.1008 0.6176 1.0000
0.250 0.6649 0.00721 0.00223 -0.1002 0.6030 1.0000
0.500 0.6902 0.00736 0.00228 -0.0996 0.5883 1.0000
1.000 0.7410 0.00766 0.00241 -0.0987 0.5580 1.0000
1.250 0.7665 0.00782 0.00250 -0.0982 0.5432 1.0000
1.500 0.7917 0.00799 0.00259 -0.0977 0.5264 1.0000
1.750 0.8170 0.00817 0.00268 -0.0972 0.5084 1.0000
2.000 0.8422 0.00836 0.00280 -0.0968 0.4896 1.0000
2.250 0.8667 0.00859 0.00293 -0.0962 0.4677 1.0000
2.500 0.8908 0.00886 0.00307 -0.0956 0.4421 1.0000
2.750 0.9144 0.00917 0.00325 -0.0949 0.4159 1.0000
3.000 0.9384 0.00947 0.00344 -0.0943 0.3939 1.0000
3.250 0.9626 0.00976 0.00364 -0.0938 0.3775 1.0000
3.500 0.9869 0.01005 0.00386 -0.0933 0.3638 1.0000
3.750 1.0114 0.01033 0.00408 -0.0928 0.3527 1.0000
4.000 1.0357 0.01062 0.00432 -0.0923 0.3434 1.0000
4.250 1.0608 0.01085 0.00454 -0.0920 0.3354 1.0000
4.750 1.1100 0.01137 0.00503 -0.0912 0.3190 1.0000
5.000 1.1337 0.01167 0.00530 -0.0906 0.3097 1.0000
5.250 1.1583 0.01191 0.00554 -0.0903 0.3004 1.0000
5.500 1.1825 0.01217 0.00580 -0.0898 0.2915 1.0000
5.750 1.2060 0.01247 0.00607 -0.0893 0.2818 1.0000
6.000 1.2305 0.01269 0.00632 -0.0889 0.2719 1.0000
6.250 1.2539 0.01298 0.00659 -0.0884 0.2604 1.0000
6.500 1.2767 0.01330 0.00689 -0.0878 0.2489 1.0000
6.750 1.2991 0.01363 0.00719 -0.0871 0.2345 1.0000
7.000 1.3205 0.01403 0.00754 -0.0863 0.2158 1.0000
7.250 1.3400 0.01455 0.00795 -0.0852 0.1959 1.0000
7.500 1.3584 0.01512 0.00844 -0.0840 0.1783 1.0000
7.750 1.3763 0.01571 0.00896 -0.0827 0.1623 1.0000
8.000 1.3919 0.01638 0.00954 -0.0810 0.1424 1.0000
8.250 1.4012 0.01737 0.01031 -0.0783 0.1045 1.0000
8.500 1.4061 0.01868 0.01138 -0.0751 0.0762 1.0000
8.750 1.4139 0.01981 0.01239 -0.0724 0.0535 1.0000
9.000 1.4127 0.02155 0.01389 -0.0686 0.0244 1.0000
9.250 1.4217 0.02264 0.01502 -0.0663 0.0210 1.0000
9.500 1.4330 0.02361 0.01607 -0.0644 0.0197 1.0000
9.750 1.4430 0.02468 0.01723 -0.0625 0.0187 1.0000
10.000 1.4507 0.02596 0.01860 -0.0605 0.0178 1.0000
10.250 1.4547 0.02756 0.02029 -0.0583 0.0169 1.0000
10.500 1.4594 0.02918 0.02202 -0.0563 0.0163 1.0000
10.750 1.4658 0.03072 0.02366 -0.0548 0.0159 1.0000
11.000 1.4703 0.03251 0.02556 -0.0533 0.0155 1.0000
11.250 1.4729 0.03453 0.02768 -0.0519 0.0151 1.0000
11.500 1.4738 0.03679 0.03004 -0.0506 0.0147 1.0000
11.750 1.4731 0.03930 0.03266 -0.0494 0.0144 1.0000
12.000 1.4702 0.04213 0.03559 -0.0485 0.0142 1.0000
12.250 1.4652 0.04533 0.03890 -0.0477 0.0139 1.0000
12.500 1.4580 0.04890 0.04258 -0.0472 0.0137 1.0000
12.750 1.4487 0.05291 0.04670 -0.0470 0.0135 1.0000
13.000 1.4374 0.05732 0.05123 -0.0470 0.0134 1.0000
13.250 1.4254 0.06191 0.05593 -0.0471 0.0132 1.0000
13.500 1.4189 0.06596 0.06008 -0.0474 0.0131 1.0000
13.750 1.4163 0.06964 0.06387 -0.0479 0.0130 1.0000
14.000 1.4127 0.07348 0.06782 -0.0485 0.0128 1.0000
14.250 1.4088 0.07743 0.07188 -0.0493 0.0127 1.0000
14.500 1.4044 0.08149 0.07604 -0.0500 0.0125 1.0000
14.750 1.4000 0.08559 0.08024 -0.0509 0.0123 1.0000
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Polar data table (+)
Polar graphs
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