N-11 (n11-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-11 (n11-il) Reynolds number: 500,000 Max Cl/Cd: 93.9 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n11-il-500000-n5.txt Download as CSV file: xf-n11-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3919 0.09491 0.09256 -0.0417 1.0000 0.0161
-11.500 -0.3906 0.09275 0.09043 -0.0417 1.0000 0.0163
-11.000 -0.5417 0.02918 0.02558 -0.1022 0.9755 0.0201
-10.750 -0.5180 0.02709 0.02331 -0.1037 0.9710 0.0205
-10.500 -0.4902 0.02635 0.02253 -0.1044 0.9653 0.0209
-10.250 -0.4594 0.02561 0.02171 -0.1058 0.9614 0.0213
-10.000 -0.4366 0.02471 0.02069 -0.1056 0.9532 0.0218
-9.750 -0.4098 0.02342 0.01921 -0.1063 0.9480 0.0223
-9.500 -0.3873 0.02223 0.01783 -0.1060 0.9391 0.0229
-9.250 -0.3607 0.02106 0.01644 -0.1064 0.9324 0.0237
-9.000 -0.3369 0.02002 0.01517 -0.1060 0.9222 0.0243
-8.750 -0.3111 0.01902 0.01396 -0.1060 0.9126 0.0247
-8.500 -0.2845 0.01823 0.01296 -0.1059 0.9023 0.0251
-8.250 -0.2577 0.01772 0.01228 -0.1057 0.8905 0.0254
-8.000 -0.2338 0.01606 0.01039 -0.1055 0.8790 0.0261
-7.750 -0.2077 0.01527 0.00945 -0.1052 0.8681 0.0265
-7.500 -0.1813 0.01466 0.00870 -0.1050 0.8582 0.0269
-7.250 -0.1548 0.01412 0.00805 -0.1047 0.8486 0.0273
-7.000 -0.1281 0.01364 0.00746 -0.1045 0.8401 0.0278
-6.750 -0.1012 0.01324 0.00695 -0.1042 0.8318 0.0284
-6.500 -0.0742 0.01284 0.00646 -0.1040 0.8247 0.0290
-6.250 -0.0473 0.01244 0.00595 -0.1037 0.8168 0.0294
-6.000 -0.0204 0.01206 0.00548 -0.1034 0.8083 0.0298
-5.750 0.0064 0.01174 0.00505 -0.1031 0.7991 0.0302
-5.500 0.0335 0.01142 0.00467 -0.1029 0.7906 0.0305
-5.250 0.0606 0.01115 0.00432 -0.1026 0.7825 0.0309
-5.000 0.0878 0.01089 0.00400 -0.1024 0.7735 0.0312
-4.750 0.1150 0.01066 0.00370 -0.1021 0.7647 0.0316
-4.500 0.1423 0.01045 0.00344 -0.1019 0.7550 0.0319
-4.250 0.1696 0.01024 0.00317 -0.1017 0.7448 0.0324
-4.000 0.1965 0.00998 0.00285 -0.1014 0.7339 0.0336
-3.750 0.2238 0.00981 0.00263 -0.1012 0.7216 0.0345
-3.500 0.2509 0.00968 0.00244 -0.1009 0.7067 0.0354
-3.250 0.2777 0.00961 0.00227 -0.1006 0.6894 0.0364
-3.000 0.3045 0.00955 0.00213 -0.1003 0.6723 0.0376
-2.750 0.3315 0.00951 0.00201 -0.1000 0.6579 0.0390
-2.500 0.3586 0.00949 0.00193 -0.0998 0.6443 0.0410
-2.250 0.3857 0.00943 0.00185 -0.0996 0.6312 0.0485
-2.000 0.4124 0.00932 0.00182 -0.0994 0.6182 0.0842
-1.750 0.4392 0.00926 0.00180 -0.0992 0.6054 0.1144
-1.500 0.4659 0.00918 0.00181 -0.0990 0.5929 0.1559
-1.250 0.4927 0.00916 0.00183 -0.0988 0.5810 0.1889
-1.000 0.5199 0.00914 0.00185 -0.0987 0.5697 0.2178
-0.750 0.5467 0.00910 0.00187 -0.0986 0.5580 0.2569
-0.500 0.5730 0.00898 0.00193 -0.0984 0.5447 0.3402
-0.250 0.5982 0.00870 0.00201 -0.0982 0.5302 0.4922
0.000 0.6224 0.00842 0.00211 -0.0976 0.5141 0.6449
0.250 0.6594 0.00785 0.00225 -0.0992 0.4949 1.0000
0.500 0.6848 0.00801 0.00232 -0.0988 0.4784 1.0000
0.750 0.7103 0.00818 0.00239 -0.0983 0.4621 1.0000
1.000 0.7353 0.00839 0.00248 -0.0978 0.4427 1.0000
1.250 0.7599 0.00863 0.00259 -0.0973 0.4174 1.0000
1.500 0.7839 0.00893 0.00272 -0.0966 0.3906 1.0000
1.750 0.8083 0.00921 0.00287 -0.0961 0.3697 1.0000
2.000 0.8329 0.00948 0.00304 -0.0956 0.3525 1.0000
2.250 0.8579 0.00972 0.00320 -0.0952 0.3393 1.0000
2.500 0.8832 0.00994 0.00336 -0.0948 0.3292 1.0000
2.750 0.9086 0.01015 0.00353 -0.0945 0.3214 1.0000
3.000 0.9343 0.01034 0.00369 -0.0942 0.3153 1.0000
3.250 0.9599 0.01053 0.00387 -0.0939 0.3091 1.0000
3.750 1.0109 0.01093 0.00424 -0.0934 0.2979 1.0000
4.000 1.0361 0.01114 0.00445 -0.0931 0.2915 1.0000
4.250 1.0611 0.01137 0.00466 -0.0927 0.2849 1.0000
4.500 1.0862 0.01159 0.00487 -0.0924 0.2766 1.0000
4.750 1.1108 0.01183 0.00509 -0.0920 0.2691 1.0000
5.000 1.1349 0.01210 0.00534 -0.0916 0.2580 1.0000
5.250 1.1585 0.01241 0.00559 -0.0910 0.2427 1.0000
5.500 1.1817 0.01274 0.00586 -0.0905 0.2264 1.0000
5.750 1.2041 0.01312 0.00617 -0.0898 0.2087 1.0000
6.000 1.2254 0.01357 0.00653 -0.0890 0.1904 1.0000
6.250 1.2459 0.01406 0.00693 -0.0880 0.1742 1.0000
6.500 1.2666 0.01453 0.00735 -0.0871 0.1612 1.0000
6.750 1.2872 0.01499 0.00778 -0.0862 0.1495 1.0000
7.000 1.3050 0.01562 0.00831 -0.0848 0.1284 1.0000
7.250 1.3150 0.01678 0.00915 -0.0824 0.0847 1.0000
7.500 1.3298 0.01745 0.00978 -0.0805 0.0728 1.0000
7.750 1.3457 0.01805 0.01037 -0.0788 0.0630 1.0000
8.250 1.3589 0.02048 0.01252 -0.0730 0.0170 1.0000
8.500 1.3732 0.02120 0.01329 -0.0713 0.0151 1.0000
8.750 1.3862 0.02201 0.01416 -0.0695 0.0137 1.0000
9.000 1.3986 0.02288 0.01510 -0.0677 0.0126 1.0000
9.250 1.4123 0.02367 0.01596 -0.0662 0.0121 1.0000
9.500 1.4249 0.02456 0.01694 -0.0646 0.0115 1.0000
9.750 1.4363 0.02555 0.01801 -0.0630 0.0110 1.0000
10.000 1.4466 0.02665 0.01919 -0.0614 0.0105 1.0000
10.250 1.4548 0.02795 0.02057 -0.0597 0.0100 1.0000
10.500 1.4598 0.02956 0.02228 -0.0579 0.0095 1.0000
10.750 1.4683 0.03095 0.02375 -0.0566 0.0092 1.0000
11.000 1.4762 0.03243 0.02533 -0.0554 0.0089 1.0000
11.250 1.4824 0.03411 0.02711 -0.0542 0.0086 1.0000
11.500 1.4871 0.03599 0.02908 -0.0531 0.0084 1.0000
11.750 1.4909 0.03802 0.03120 -0.0520 0.0082 1.0000
12.000 1.4931 0.04026 0.03354 -0.0511 0.0079 1.0000
12.250 1.4942 0.04271 0.03609 -0.0503 0.0078 1.0000
12.500 1.4941 0.04538 0.03886 -0.0497 0.0076 1.0000
12.750 1.4921 0.04835 0.04194 -0.0493 0.0074 1.0000
13.000 1.4883 0.05170 0.04540 -0.0491 0.0073 1.0000
13.250 1.4823 0.05547 0.04929 -0.0492 0.0072 1.0000
13.500 1.4738 0.05968 0.05363 -0.0495 0.0071 1.0000
13.750 1.4627 0.06443 0.05851 -0.0501 0.0070 1.0000
14.000 1.4547 0.06891 0.06310 -0.0509 0.0069 1.0000
14.250 1.4474 0.07337 0.06769 -0.0517 0.0068 1.0000
14.500 1.4393 0.07806 0.07250 -0.0528 0.0068 1.0000
14.750 1.4301 0.08300 0.07757 -0.0540 0.0067 1.0000
15.000 1.4204 0.08812 0.08281 -0.0554 0.0066 1.0000
15.250 1.4101 0.09337 0.08817 -0.0568 0.0065 1.0000
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