EPPLER 341 AIRFOIL (e341-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 341 AIRFOIL (e341-il) Reynolds number: 50,000 Max Cl/Cd: 23.12 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e341-il-50000-n5.txt Download as CSV file: xf-e341-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 341 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3168 0.12886 0.12282 -0.0061 1.0000 0.1110
-11.500 -0.3234 0.12660 0.12060 -0.0078 1.0000 0.1147
-11.250 -0.4815 0.13523 0.12879 0.0015 1.0000 0.1022
-11.000 -0.4579 0.13062 0.12417 0.0043 1.0000 0.1057
-10.750 -0.4517 0.12699 0.12058 0.0034 1.0000 0.1086
-10.500 -0.4498 0.12331 0.11696 0.0016 1.0000 0.1115
-10.250 -0.4679 0.12003 0.11380 -0.0042 1.0000 0.1163
-9.750 -0.4633 0.11102 0.10495 -0.0073 1.0000 0.1187
-9.250 -0.4755 0.09153 0.08528 -0.0220 1.0000 0.0496
-9.000 -0.4740 0.08770 0.08150 -0.0225 1.0000 0.0489
-8.750 -0.4775 0.08381 0.07764 -0.0230 1.0000 0.0480
-8.500 -0.4848 0.08001 0.07384 -0.0231 1.0000 0.0472
-8.250 -0.4937 0.07641 0.07024 -0.0224 1.0000 0.0463
-8.000 -0.5009 0.07271 0.06648 -0.0216 1.0000 0.0453
-7.750 -0.5074 0.06896 0.06262 -0.0203 1.0000 0.0442
-7.250 -0.5228 0.06125 0.05426 -0.0152 1.0000 0.0410
-7.000 -0.5190 0.05839 0.05134 -0.0131 1.0000 0.0407
-6.750 -0.5177 0.05585 0.04873 -0.0105 1.0000 0.0404
-6.500 -0.4953 0.05201 0.04455 -0.0120 0.9538 0.0400
-6.250 -0.4682 0.04820 0.04028 -0.0134 0.9147 0.0397
-6.000 -0.4415 0.04479 0.03633 -0.0139 0.8832 0.0396
-5.750 -0.4170 0.04189 0.03287 -0.0133 0.8547 0.0396
-5.500 -0.3934 0.03940 0.02982 -0.0121 0.8298 0.0400
-5.250 -0.3701 0.03726 0.02710 -0.0106 0.8064 0.0413
-5.000 -0.3468 0.03566 0.02533 -0.0097 0.7851 0.0436
-4.750 -0.3211 0.03409 0.02340 -0.0087 0.7661 0.0460
-4.500 -0.2910 0.03240 0.02128 -0.0081 0.7482 0.0482
-4.250 -0.2563 0.03075 0.01929 -0.0083 0.7309 0.0508
-4.000 -0.2218 0.02957 0.01799 -0.0089 0.7147 0.0569
-3.750 -0.1826 0.02836 0.01658 -0.0100 0.6993 0.0646
-3.500 -0.1517 0.02740 0.01547 -0.0100 0.6845 0.0762
-3.250 -0.1258 0.02648 0.01449 -0.0093 0.6711 0.0946
-3.000 -0.0514 0.02367 0.01521 -0.0131 0.6569 0.7884
-2.750 0.1003 0.02533 0.01562 -0.0301 0.6357 1.0000
-2.500 0.1234 0.02519 0.01515 -0.0298 0.6244 1.0000
-2.250 0.1460 0.02508 0.01471 -0.0293 0.6147 1.0000
-2.000 0.1697 0.02501 0.01440 -0.0292 0.6039 1.0000
-1.750 0.1930 0.02496 0.01409 -0.0288 0.5947 1.0000
-1.500 0.2166 0.02494 0.01385 -0.0285 0.5856 1.0000
-1.250 0.2404 0.02496 0.01367 -0.0283 0.5770 1.0000
-1.000 0.2639 0.02500 0.01350 -0.0279 0.5687 1.0000
-0.750 0.2876 0.02508 0.01342 -0.0276 0.5608 1.0000
-0.500 0.3112 0.02517 0.01336 -0.0273 0.5531 1.0000
-0.250 0.3347 0.02529 0.01331 -0.0269 0.5465 1.0000
0.000 0.3586 0.02547 0.01340 -0.0267 0.5387 1.0000
0.250 0.3822 0.02560 0.01335 -0.0261 0.5330 1.0000
0.500 0.4065 0.02587 0.01359 -0.0262 0.5255 1.0000
0.750 0.4302 0.02608 0.01369 -0.0258 0.5194 1.0000
1.000 0.4538 0.02631 0.01382 -0.0254 0.5140 1.0000
1.250 0.4775 0.02667 0.01417 -0.0253 0.5070 1.0000
1.500 0.5009 0.02691 0.01432 -0.0248 0.5018 1.0000
1.750 0.5243 0.02727 0.01465 -0.0245 0.4963 1.0000
2.000 0.5474 0.02772 0.01512 -0.0243 0.4902 1.0000
2.250 0.5705 0.02801 0.01535 -0.0237 0.4854 1.0000
2.500 0.5932 0.02846 0.01579 -0.0233 0.4803 1.0000
2.750 0.6154 0.02904 0.01643 -0.0230 0.4743 1.0000
3.000 0.6378 0.02942 0.01680 -0.0224 0.4698 1.0000
3.250 0.6601 0.02984 0.01719 -0.0218 0.4656 1.0000
3.500 0.6801 0.03068 0.01817 -0.0215 0.4593 1.0000
3.750 0.7013 0.03119 0.01869 -0.0208 0.4546 1.0000
4.000 0.7236 0.03151 0.01899 -0.0199 0.4510 1.0000
4.250 0.7409 0.03263 0.02029 -0.0194 0.4449 1.0000
4.500 0.7600 0.03337 0.02110 -0.0186 0.4399 1.0000
4.750 0.7811 0.03379 0.02152 -0.0177 0.4361 1.0000
5.000 0.7977 0.03483 0.02271 -0.0168 0.4311 1.0000
5.250 0.8122 0.03602 0.02405 -0.0158 0.4254 1.0000
5.500 0.8313 0.03660 0.02467 -0.0147 0.4213 1.0000
5.750 0.8519 0.03703 0.02510 -0.0136 0.4178 1.0000
6.000 0.8560 0.03915 0.02751 -0.0121 0.4108 1.0000
6.250 0.8714 0.03999 0.02843 -0.0108 0.4063 1.0000
6.500 0.8930 0.04025 0.02870 -0.0096 0.4030 1.0000
6.750 0.8861 0.04308 0.03178 -0.0073 0.3957 1.0000
7.000 0.8960 0.04426 0.03308 -0.0055 0.3909 1.0000
7.250 0.9173 0.04445 0.03331 -0.0041 0.3876 1.0000
7.500 0.8898 0.04851 0.03758 -0.0005 0.3794 1.0000
7.750 0.8957 0.04978 0.03893 0.0017 0.3747 1.0000
8.000 0.9194 0.04970 0.03890 0.0030 0.3716 1.0000
8.500 0.8552 0.05736 0.04669 0.0112 0.3572 1.0000
8.750 0.8904 0.05645 0.04588 0.0121 0.3550 1.0000
9.750 0.7252 0.07798 0.06729 0.0204 0.3191 1.0000
10.000 0.7250 0.08018 0.06953 0.0214 0.3129 1.0000
10.250 0.7456 0.08024 0.06968 0.0229 0.3098 1.0000
10.500 0.7144 0.08610 0.07553 0.0223 0.2998 1.0000
10.750 0.7317 0.08663 0.07616 0.0235 0.2957 1.0000
11.000 0.7131 0.09143 0.08097 0.0229 0.2874 1.0000
11.250 0.7233 0.09290 0.08253 0.0235 0.2822 1.0000
11.750 0.7207 0.09877 0.08853 0.0232 0.2688 1.0000
12.000 0.7431 0.09877 0.08864 0.0243 0.2653 1.0000
12.250 0.7208 0.10459 0.09448 0.0226 0.2558 1.0000
12.500 0.7405 0.10494 0.09496 0.0235 0.2517 1.0000
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Polar data table (+)
Polar graphs
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