NACA 2414 (n2414-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2414 (n2414-il) Reynolds number: 50,000 Max Cl/Cd: 29.23 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n2414-il-50000.txt Download as CSV file: xf-n2414-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2414
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3825 0.10398 0.09611 -0.0137 1.0000 0.3671
-8.750 -0.5753 0.07718 0.06972 -0.0398 1.0000 0.1960
-8.500 -0.5903 0.07225 0.06477 -0.0393 1.0000 0.1934
-8.250 -0.6074 0.06745 0.05995 -0.0382 1.0000 0.1919
-8.000 -0.6270 0.06252 0.05492 -0.0368 1.0000 0.1905
-7.750 -0.6441 0.05772 0.04991 -0.0350 1.0000 0.1899
-7.500 -0.6555 0.05323 0.04512 -0.0331 1.0000 0.1904
-7.250 -0.6624 0.04905 0.04051 -0.0311 1.0000 0.1926
-7.000 -0.6613 0.04554 0.03659 -0.0291 1.0000 0.1965
-6.750 -0.6454 0.04405 0.03519 -0.0274 1.0000 0.2030
-6.500 -0.6384 0.04119 0.03185 -0.0257 1.0000 0.2097
-6.250 -0.6236 0.03937 0.02999 -0.0241 1.0000 0.2174
-6.000 -0.6102 0.03731 0.02753 -0.0227 1.0000 0.2271
-5.750 -0.5927 0.03593 0.02621 -0.0213 1.0000 0.2373
-5.500 -0.5759 0.03426 0.02430 -0.0201 1.0000 0.2494
-5.250 -0.5578 0.03290 0.02269 -0.0190 1.0000 0.2636
-5.000 -0.5386 0.03183 0.02159 -0.0179 1.0000 0.2793
-4.750 -0.5190 0.03079 0.02054 -0.0168 1.0000 0.2966
-4.500 -0.4988 0.02984 0.01954 -0.0159 1.0000 0.3166
-4.250 -0.4783 0.02903 0.01886 -0.0149 1.0000 0.3380
-4.000 -0.4578 0.02831 0.01822 -0.0139 1.0000 0.3626
-3.750 -0.4372 0.02761 0.01756 -0.0130 1.0000 0.3911
-3.500 -0.4169 0.02705 0.01710 -0.0120 1.0000 0.4226
-3.250 -0.3970 0.02657 0.01681 -0.0108 1.0000 0.4564
-3.000 -0.3777 0.02618 0.01658 -0.0096 1.0000 0.4951
-2.750 -0.3592 0.02588 0.01651 -0.0081 1.0000 0.5370
-2.500 -0.3412 0.02566 0.01652 -0.0064 1.0000 0.5848
-2.250 -0.3245 0.02550 0.01665 -0.0042 1.0000 0.6385
-2.000 -0.3101 0.02540 0.01685 -0.0013 1.0000 0.7009
-1.750 -0.2997 0.02540 0.01717 0.0029 1.0000 0.7715
-1.500 -0.2877 0.02559 0.01766 0.0076 1.0000 0.8603
-1.250 -0.1519 0.02739 0.01916 -0.0120 1.0000 1.0000
-1.000 -0.1758 0.02659 0.01821 -0.0080 1.0000 1.0000
-0.750 -0.1385 0.02713 0.01845 -0.0129 0.9894 1.0000
-0.500 -0.0886 0.02800 0.01903 -0.0193 0.9742 1.0000
-0.250 -0.0411 0.02885 0.01964 -0.0247 0.9589 1.0000
0.000 0.0025 0.02963 0.02024 -0.0292 0.9437 1.0000
0.250 0.0438 0.03037 0.02083 -0.0330 0.9283 1.0000
0.500 0.0823 0.03109 0.02141 -0.0362 0.9130 1.0000
0.750 0.1194 0.03177 0.02199 -0.0389 0.8977 1.0000
1.000 0.1561 0.03245 0.02258 -0.0414 0.8829 1.0000
1.250 0.1948 0.03309 0.02314 -0.0441 0.8685 1.0000
1.500 0.2417 0.03363 0.02363 -0.0478 0.8553 1.0000
1.750 0.2685 0.03426 0.02421 -0.0483 0.8396 1.0000
2.000 0.2953 0.03492 0.02484 -0.0488 0.8243 1.0000
2.250 0.3233 0.03559 0.02549 -0.0494 0.8094 1.0000
2.500 0.3545 0.03620 0.02609 -0.0503 0.7950 1.0000
2.750 0.3943 0.03658 0.02648 -0.0522 0.7817 1.0000
3.000 0.4365 0.03678 0.02672 -0.0541 0.7682 1.0000
3.250 0.4573 0.03753 0.02748 -0.0533 0.7525 1.0000
3.500 0.4806 0.03823 0.02820 -0.0528 0.7371 1.0000
3.750 0.5071 0.03883 0.02883 -0.0525 0.7221 1.0000
4.000 0.5409 0.03909 0.02915 -0.0529 0.7078 1.0000
4.250 0.5998 0.03799 0.02815 -0.0552 0.6966 1.0000
4.500 0.6204 0.03863 0.02883 -0.0538 0.6804 1.0000
4.750 0.6428 0.03918 0.02943 -0.0526 0.6642 1.0000
5.000 0.6673 0.03960 0.02992 -0.0514 0.6480 1.0000
5.250 0.6945 0.03980 0.03020 -0.0503 0.6318 1.0000
5.500 0.7239 0.03981 0.03029 -0.0493 0.6155 1.0000
5.750 0.7558 0.03958 0.03014 -0.0482 0.5989 1.0000
6.000 0.7890 0.03919 0.02982 -0.0472 0.5816 1.0000
6.250 0.8223 0.03873 0.02944 -0.0460 0.5635 1.0000
6.500 0.8565 0.03815 0.02892 -0.0449 0.5444 1.0000
6.750 0.8937 0.03732 0.02812 -0.0439 0.5243 1.0000
7.000 0.9352 0.03621 0.02695 -0.0432 0.5031 1.0000
7.250 0.9530 0.03668 0.02748 -0.0409 0.4805 1.0000
7.500 0.9764 0.03673 0.02755 -0.0389 0.4568 1.0000
7.750 1.0137 0.03591 0.02654 -0.0381 0.4319 1.0000
8.000 1.0253 0.03674 0.02746 -0.0352 0.4073 1.0000
8.250 1.0584 0.03624 0.02671 -0.0341 0.3811 1.0000
8.500 1.0672 0.03731 0.02788 -0.0311 0.3569 1.0000
8.750 1.0937 0.03742 0.02772 -0.0297 0.3315 1.0000
9.000 1.1041 0.03868 0.02903 -0.0270 0.3093 1.0000
9.250 1.1186 0.03981 0.03013 -0.0247 0.2878 1.0000
9.500 1.1374 0.04093 0.03110 -0.0231 0.2679 1.0000
9.750 1.1553 0.04233 0.03239 -0.0215 0.2502 1.0000
10.000 1.1663 0.04414 0.03427 -0.0193 0.2353 1.0000
10.250 1.1720 0.04640 0.03671 -0.0167 0.2231 1.0000
10.500 1.1824 0.04855 0.03893 -0.0148 0.2118 1.0000
10.750 1.2032 0.05045 0.04070 -0.0140 0.2002 1.0000
11.000 1.1903 0.05362 0.04432 -0.0101 0.1944 1.0000
11.250 1.2121 0.05568 0.04627 -0.0095 0.1848 1.0000
11.500 1.1884 0.05944 0.05048 -0.0052 0.1821 1.0000
11.750 1.1605 0.06334 0.05468 -0.0012 0.1802 1.0000
12.000 1.1237 0.06835 0.05995 0.0018 0.1799 1.0000
12.250 1.0714 0.07576 0.06761 0.0025 0.1818 1.0000
12.500 1.0139 0.08592 0.07793 -0.0001 0.1844 1.0000
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Polar data table (+)
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