N-11 (n11-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-11 (n11-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.61 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n11-il-1000000-n5.txt Download as CSV file: xf-n11-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -1.0256 0.03176 0.02915 -0.0990 0.9974 0.0108
-15.250 -1.0076 0.02913 0.02634 -0.1011 0.9956 0.0113
-15.000 -0.9854 0.02713 0.02419 -0.1028 0.9943 0.0118
-14.750 -0.9652 0.02547 0.02237 -0.1034 0.9922 0.0122
-14.500 -0.9429 0.02401 0.02076 -0.1040 0.9902 0.0127
-14.250 -0.9149 0.02343 0.02016 -0.1046 0.9889 0.0133
-14.000 -0.8855 0.02298 0.01969 -0.1053 0.9877 0.0138
-13.750 -0.8561 0.02244 0.01910 -0.1061 0.9866 0.0143
-13.500 -0.8274 0.02168 0.01825 -0.1069 0.9857 0.0148
-13.250 -0.7994 0.02077 0.01722 -0.1078 0.9846 0.0153
-13.000 -0.7762 0.01991 0.01623 -0.1075 0.9814 0.0157
-12.750 -0.7501 0.01911 0.01531 -0.1077 0.9788 0.0160
-12.500 -0.7211 0.01872 0.01489 -0.1081 0.9766 0.0164
-12.250 -0.6909 0.01856 0.01473 -0.1086 0.9748 0.0168
-12.000 -0.6619 0.01844 0.01460 -0.1088 0.9724 0.0171
-11.750 -0.6357 0.01823 0.01437 -0.1085 0.9680 0.0175
-11.500 -0.6078 0.01787 0.01396 -0.1086 0.9634 0.0178
-11.250 -0.5819 0.01742 0.01343 -0.1083 0.9568 0.0182
-11.000 -0.5557 0.01696 0.01287 -0.1081 0.9489 0.0187
-10.750 -0.5301 0.01653 0.01236 -0.1077 0.9405 0.0191
-10.500 -0.5040 0.01608 0.01180 -0.1074 0.9320 0.0195
-10.250 -0.4783 0.01565 0.01127 -0.1070 0.9205 0.0198
-10.000 -0.4520 0.01533 0.01084 -0.1066 0.9065 0.0200
-9.750 -0.4272 0.01471 0.01006 -0.1061 0.8889 0.0203
-9.500 -0.4027 0.01407 0.00927 -0.1056 0.8715 0.0208
-9.250 -0.3768 0.01376 0.00885 -0.1052 0.8568 0.0211
-8.750 -0.3238 0.01321 0.00813 -0.1046 0.8353 0.0217
-8.500 -0.2973 0.01286 0.00769 -0.1043 0.8275 0.0220
-8.250 -0.2702 0.01257 0.00733 -0.1041 0.8203 0.0224
-7.750 -0.2163 0.01189 0.00648 -0.1036 0.8076 0.0231
-7.500 -0.1892 0.01153 0.00604 -0.1034 0.8018 0.0235
-7.250 -0.1621 0.01121 0.00564 -0.1032 0.7958 0.0238
-7.000 -0.1348 0.01090 0.00526 -0.1030 0.7884 0.0241
-6.750 -0.1075 0.01067 0.00496 -0.1028 0.7804 0.0245
-6.500 -0.0798 0.01045 0.00468 -0.1026 0.7724 0.0248
-6.250 -0.0524 0.01023 0.00439 -0.1024 0.7653 0.0250
-6.000 -0.0247 0.00999 0.00411 -0.1023 0.7574 0.0251
-5.750 0.0028 0.00980 0.00385 -0.1021 0.7483 0.0253
-5.500 0.0303 0.00960 0.00359 -0.1019 0.7376 0.0254
-5.250 0.0574 0.00924 0.00315 -0.1018 0.7281 0.0258
-5.000 0.0847 0.00899 0.00283 -0.1015 0.7167 0.0262
-4.750 0.1119 0.00881 0.00258 -0.1013 0.7015 0.0266
-4.500 0.1391 0.00868 0.00236 -0.1011 0.6845 0.0271
-4.250 0.1661 0.00859 0.00219 -0.1008 0.6651 0.0275
-4.000 0.1930 0.00855 0.00204 -0.1005 0.6451 0.0280
-3.750 0.2201 0.00851 0.00193 -0.1003 0.6278 0.0286
-3.500 0.2476 0.00847 0.00182 -0.1002 0.6138 0.0293
-3.250 0.2753 0.00842 0.00173 -0.1000 0.6021 0.0300
-3.000 0.3029 0.00839 0.00164 -0.0999 0.5905 0.0306
-2.750 0.3305 0.00838 0.00157 -0.0998 0.5786 0.0312
-2.500 0.3581 0.00838 0.00152 -0.0997 0.5666 0.0317
-2.250 0.3860 0.00837 0.00147 -0.0997 0.5563 0.0322
-2.000 0.4137 0.00836 0.00142 -0.0996 0.5465 0.0338
-1.750 0.4412 0.00837 0.00140 -0.0995 0.5341 0.0366
-1.500 0.4686 0.00837 0.00138 -0.0994 0.5206 0.0443
-1.250 0.4957 0.00829 0.00138 -0.0993 0.5065 0.0870
-1.000 0.5230 0.00827 0.00140 -0.0992 0.4926 0.1135
-0.750 0.5498 0.00827 0.00144 -0.0991 0.4755 0.1532
-0.500 0.5765 0.00831 0.00149 -0.0990 0.4560 0.1868
-0.250 0.6032 0.00838 0.00155 -0.0988 0.4355 0.2136
0.000 0.6293 0.00844 0.00163 -0.0986 0.4110 0.2637
0.250 0.6550 0.00848 0.00173 -0.0984 0.3852 0.3351
0.500 0.6806 0.00847 0.00186 -0.0982 0.3646 0.4291
0.750 0.7059 0.00833 0.00200 -0.0980 0.3479 0.5728
1.000 0.7324 0.00759 0.00222 -0.0977 0.3319 0.9895
1.250 0.7624 0.00779 0.00233 -0.0983 0.3184 1.0000
1.500 0.7888 0.00793 0.00242 -0.0981 0.3104 1.0000
1.750 0.8151 0.00808 0.00252 -0.0979 0.3041 1.0000
2.000 0.8419 0.00820 0.00262 -0.0977 0.2995 1.0000
2.250 0.8685 0.00832 0.00272 -0.0976 0.2944 1.0000
2.500 0.8949 0.00848 0.00284 -0.0974 0.2890 1.0000
2.750 0.9216 0.00860 0.00295 -0.0973 0.2848 1.0000
3.000 0.9481 0.00874 0.00306 -0.0972 0.2792 1.0000
3.250 0.9741 0.00893 0.00321 -0.0970 0.2721 1.0000
3.500 1.0006 0.00906 0.00334 -0.0969 0.2661 1.0000
3.750 1.0265 0.00925 0.00348 -0.0967 0.2590 1.0000
4.000 1.0525 0.00943 0.00364 -0.0965 0.2504 1.0000
4.250 1.0775 0.00968 0.00382 -0.0962 0.2364 1.0000
4.500 1.1014 0.01001 0.00404 -0.0957 0.2165 1.0000
4.750 1.1241 0.01043 0.00433 -0.0950 0.1914 1.0000
5.000 1.1473 0.01080 0.00461 -0.0944 0.1754 1.0000
5.250 1.1709 0.01114 0.00488 -0.0939 0.1633 1.0000
5.500 1.1946 0.01147 0.00516 -0.0934 0.1529 1.0000
5.750 1.2178 0.01181 0.00546 -0.0929 0.1428 1.0000
6.000 1.2399 0.01224 0.00580 -0.0921 0.1257 1.0000
6.500 1.2762 0.01365 0.00688 -0.0895 0.0729 1.0000
6.750 1.2979 0.01405 0.00727 -0.0887 0.0647 1.0000
7.000 1.3157 0.01472 0.00782 -0.0873 0.0471 1.0000
7.250 1.3269 0.01586 0.00877 -0.0849 0.0155 1.0000
7.500 1.3462 0.01633 0.00925 -0.0837 0.0130 1.0000
7.750 1.3650 0.01673 0.00968 -0.0825 0.0121 1.0000
8.000 1.3830 0.01717 0.01016 -0.0811 0.0113 1.0000
8.250 1.4000 0.01767 0.01068 -0.0796 0.0105 1.0000
8.500 1.4160 0.01823 0.01128 -0.0780 0.0096 1.0000
8.750 1.4326 0.01876 0.01184 -0.0765 0.0092 1.0000
9.000 1.4490 0.01930 0.01242 -0.0751 0.0088 1.0000
9.250 1.4647 0.01989 0.01306 -0.0736 0.0083 1.0000
9.500 1.4794 0.02055 0.01375 -0.0721 0.0079 1.0000
9.750 1.4932 0.02127 0.01451 -0.0705 0.0075 1.0000
10.000 1.5054 0.02212 0.01541 -0.0687 0.0071 1.0000
10.250 1.5176 0.02299 0.01633 -0.0671 0.0069 1.0000
10.500 1.5303 0.02384 0.01725 -0.0656 0.0067 1.0000
10.750 1.5421 0.02478 0.01824 -0.0642 0.0065 1.0000
11.000 1.5532 0.02581 0.01933 -0.0628 0.0063 1.0000
11.250 1.5635 0.02693 0.02050 -0.0614 0.0061 1.0000
11.500 1.5733 0.02812 0.02176 -0.0601 0.0059 1.0000
11.750 1.5822 0.02944 0.02313 -0.0588 0.0057 1.0000
12.000 1.5900 0.03088 0.02463 -0.0576 0.0055 1.0000
12.250 1.5961 0.03253 0.02635 -0.0564 0.0053 1.0000
12.500 1.5999 0.03445 0.02835 -0.0552 0.0051 1.0000
12.750 1.6030 0.03648 0.03046 -0.0541 0.0050 1.0000
13.000 1.6074 0.03846 0.03252 -0.0532 0.0049 1.0000
13.250 1.6102 0.04065 0.03480 -0.0524 0.0048 1.0000
13.500 1.6120 0.04304 0.03728 -0.0518 0.0047 1.0000
13.750 1.6126 0.04563 0.03996 -0.0513 0.0047 1.0000
14.000 1.6119 0.04848 0.04291 -0.0510 0.0046 1.0000
14.250 1.6102 0.05157 0.04610 -0.0508 0.0045 1.0000
14.500 1.6076 0.05488 0.04950 -0.0509 0.0044 1.0000
14.750 1.6032 0.05849 0.05322 -0.0511 0.0044 1.0000
15.000 1.5977 0.06237 0.05721 -0.0515 0.0043 1.0000
15.250 1.5911 0.06652 0.06146 -0.0521 0.0042 1.0000
15.500 1.5828 0.07099 0.06604 -0.0529 0.0042 1.0000
15.750 1.5735 0.07565 0.07081 -0.0539 0.0041 1.0000
16.000 1.5624 0.08072 0.07600 -0.0550 0.0041 1.0000
16.250 1.5505 0.08600 0.08139 -0.0564 0.0041 1.0000
16.500 1.5368 0.09165 0.08715 -0.0579 0.0040 1.0000
16.750 1.5231 0.09736 0.09298 -0.0596 0.0040 1.0000
17.000 1.5082 0.10343 0.09916 -0.0615 0.0040 1.0000
17.250 1.4940 0.10944 0.10528 -0.0635 0.0039 1.0000
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Polar data table (+)
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