N-13 (n13-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-13 (n13-il) Reynolds number: 50,000 Max Cl/Cd: 27.72 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n13-il-50000-n5.txt Download as CSV file: xf-n13-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: N-13
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6916 0.10027 0.09268 -0.0313 1.0000 0.0567
-12.500 -0.7211 0.09000 0.08240 -0.0373 1.0000 0.0557
-12.250 -0.7538 0.08085 0.07317 -0.0427 1.0000 0.0546
-12.000 -0.7858 0.07338 0.06556 -0.0464 1.0000 0.0538
-11.750 -0.8132 0.06766 0.05965 -0.0478 1.0000 0.0534
-11.500 -0.8351 0.06322 0.05504 -0.0475 1.0000 0.0535
-11.250 -0.8545 0.05943 0.05102 -0.0458 1.0000 0.0541
-11.000 -0.8709 0.05615 0.04749 -0.0430 1.0000 0.0551
-10.750 -0.8853 0.05317 0.04419 -0.0394 1.0000 0.0565
-10.500 -0.8969 0.05018 0.04072 -0.0356 1.0000 0.0583
-10.250 -0.8912 0.04830 0.03893 -0.0335 1.0000 0.0611
-10.000 -0.8874 0.04644 0.03697 -0.0309 1.0000 0.0643
-9.750 -0.8831 0.04394 0.03411 -0.0282 1.0000 0.0682
-9.500 -0.8762 0.04245 0.03258 -0.0257 1.0000 0.0727
-9.250 -0.8687 0.04086 0.03077 -0.0231 1.0000 0.0788
-9.000 -0.8597 0.03957 0.02940 -0.0207 1.0000 0.0849
-8.750 -0.8508 0.03811 0.02761 -0.0180 1.0000 0.0932
-8.500 -0.8406 0.03699 0.02643 -0.0156 1.0000 0.1018
-8.250 -0.8258 0.03547 0.02474 -0.0138 1.0000 0.1101
-8.000 -0.8103 0.03410 0.02315 -0.0119 1.0000 0.1197
-7.750 -0.7910 0.03264 0.02171 -0.0106 1.0000 0.1281
-7.500 -0.7723 0.03132 0.02026 -0.0090 1.0000 0.1386
-7.250 -0.7562 0.03021 0.01910 -0.0072 1.0000 0.1513
-7.000 -0.7404 0.02915 0.01803 -0.0052 1.0000 0.1646
-6.750 -0.7247 0.02816 0.01698 -0.0033 1.0000 0.1790
-6.500 -0.7095 0.02724 0.01607 -0.0012 1.0000 0.1950
-6.250 -0.6952 0.02635 0.01522 0.0009 1.0000 0.2135
-6.000 -0.6813 0.02547 0.01442 0.0031 1.0000 0.2361
-5.750 -0.6677 0.02461 0.01369 0.0054 1.0000 0.2612
-5.500 -0.6553 0.02378 0.01306 0.0079 1.0000 0.2944
-5.250 -0.6437 0.02301 0.01252 0.0106 1.0000 0.3393
-5.000 -0.6317 0.02235 0.01206 0.0135 1.0000 0.3926
-4.750 -0.6190 0.02178 0.01173 0.0164 1.0000 0.4453
-4.500 -0.6049 0.02136 0.01152 0.0192 1.0000 0.4970
-4.250 -0.5894 0.02108 0.01135 0.0219 1.0000 0.5439
-4.000 -0.5726 0.02089 0.01119 0.0244 1.0000 0.5853
-3.750 -0.5559 0.02074 0.01102 0.0269 1.0000 0.6222
-3.500 -0.5381 0.02061 0.01088 0.0292 1.0000 0.6555
-3.250 -0.5183 0.02053 0.01078 0.0311 1.0000 0.6884
-3.000 -0.4959 0.02054 0.01081 0.0328 1.0000 0.7224
-2.750 -0.4696 0.02067 0.01096 0.0339 1.0000 0.7573
-2.500 -0.4393 0.02095 0.01126 0.0343 1.0000 0.7940
-2.250 -0.3994 0.02151 0.01177 0.0333 1.0000 0.8291
-2.000 -0.3575 0.02208 0.01225 0.0315 1.0000 0.8586
-1.750 -0.3164 0.02244 0.01248 0.0292 1.0000 0.8791
-1.500 -0.2786 0.02263 0.01257 0.0270 1.0000 0.8966
-1.250 -0.2413 0.02279 0.01262 0.0247 1.0000 0.9130
-1.000 -0.2035 0.02293 0.01268 0.0221 1.0000 0.9292
-0.750 -0.1645 0.02305 0.01274 0.0192 1.0000 0.9449
-0.500 -0.1243 0.02316 0.01281 0.0158 1.0000 0.9603
-0.250 -0.0809 0.02324 0.01285 0.0116 1.0000 0.9747
0.000 -0.0356 0.02329 0.01290 0.0069 1.0000 0.9892
0.250 0.0033 0.02336 0.01296 0.0031 0.9988 1.0000
0.500 0.0586 0.02331 0.01294 -0.0036 0.9822 1.0000
0.750 0.1040 0.02319 0.01287 -0.0081 0.9659 1.0000
1.000 0.1473 0.02308 0.01281 -0.0121 0.9508 1.0000
1.250 0.1885 0.02294 0.01273 -0.0155 0.9351 1.0000
1.500 0.2322 0.02276 0.01266 -0.0190 0.9197 1.0000
1.750 0.2787 0.02251 0.01254 -0.0229 0.9037 1.0000
2.000 0.3271 0.02222 0.01239 -0.0268 0.8856 1.0000
2.250 0.3705 0.02188 0.01219 -0.0294 0.8630 1.0000
2.500 0.4016 0.02160 0.01205 -0.0297 0.8341 1.0000
2.750 0.4263 0.02135 0.01190 -0.0286 0.8011 1.0000
3.000 0.4590 0.02096 0.01162 -0.0286 0.7666 1.0000
3.250 0.4948 0.02061 0.01129 -0.0290 0.7290 1.0000
3.500 0.5271 0.02042 0.01105 -0.0288 0.6863 1.0000
3.750 0.5486 0.02050 0.01107 -0.0268 0.6380 1.0000
4.000 0.5648 0.02068 0.01116 -0.0240 0.5825 1.0000
4.250 0.5799 0.02096 0.01123 -0.0211 0.5193 1.0000
4.500 0.5938 0.02142 0.01133 -0.0180 0.4567 1.0000
4.750 0.6069 0.02205 0.01168 -0.0152 0.4027 1.0000
5.000 0.6198 0.02275 0.01216 -0.0125 0.3540 1.0000
5.250 0.6326 0.02348 0.01272 -0.0099 0.3101 1.0000
5.500 0.6451 0.02426 0.01331 -0.0073 0.2715 1.0000
5.750 0.6583 0.02511 0.01399 -0.0049 0.2393 1.0000
6.000 0.6721 0.02600 0.01476 -0.0026 0.2113 1.0000
6.250 0.6876 0.02694 0.01567 -0.0006 0.1884 1.0000
6.500 0.7042 0.02793 0.01662 0.0012 0.1709 1.0000
6.750 0.7208 0.02892 0.01761 0.0031 0.1559 1.0000
7.000 0.7386 0.02997 0.01869 0.0047 0.1441 1.0000
7.250 0.7570 0.03110 0.01975 0.0062 0.1351 1.0000
7.500 0.7753 0.03222 0.02111 0.0078 0.1252 1.0000
7.750 0.7931 0.03346 0.02241 0.0094 0.1173 1.0000
8.000 0.8124 0.03487 0.02401 0.0108 0.1110 1.0000
8.250 0.8302 0.03635 0.02551 0.0122 0.1052 1.0000
8.500 0.8437 0.03784 0.02730 0.0144 0.0984 1.0000
8.750 0.8601 0.03938 0.02880 0.0158 0.0934 1.0000
9.000 0.8696 0.04142 0.03128 0.0184 0.0884 1.0000
9.250 0.8783 0.04306 0.03315 0.0209 0.0831 1.0000
9.500 0.8895 0.04487 0.03494 0.0229 0.0789 1.0000
9.750 0.8879 0.04737 0.03796 0.0265 0.0754 1.0000
10.000 0.8873 0.04954 0.04041 0.0297 0.0717 1.0000
10.250 0.8899 0.05148 0.04246 0.0324 0.0687 1.0000
10.500 0.8950 0.05373 0.04468 0.0345 0.0663 1.0000
10.750 0.8766 0.05679 0.04816 0.0389 0.0651 1.0000
11.000 0.8551 0.05974 0.05139 0.0431 0.0642 1.0000
11.250 0.8318 0.06309 0.05497 0.0462 0.0636 1.0000
11.500 0.8066 0.06713 0.05921 0.0476 0.0633 1.0000
11.750 0.7797 0.07211 0.06436 0.0474 0.0637 1.0000
12.000 0.7509 0.07826 0.07062 0.0452 0.0642 1.0000
12.250 0.7209 0.08587 0.07829 0.0411 0.0649 1.0000
12.500 0.6913 0.09508 0.08752 0.0355 0.0654 1.0000
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Polar data table (+)
Polar graphs
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