EPPLER 341 AIRFOIL (e341-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 341 AIRFOIL (e341-il) Reynolds number: 50,000 Max Cl/Cd: 13.6 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e341-il-50000.txt Download as CSV file: xf-e341-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4690 0.13367 0.12743 0.0083 1.0000 0.1979
-10.500 -0.4435 0.12820 0.12197 0.0101 1.0000 0.2075
-10.250 -0.4685 0.12702 0.12091 0.0063 1.0000 0.2148
-10.000 -0.4392 0.12158 0.11549 0.0086 1.0000 0.2275
-9.750 -0.4353 0.11783 0.11183 0.0081 1.0000 0.2371
-9.500 -0.4601 0.11636 0.11048 0.0051 1.0000 0.2480
-9.250 -0.4419 0.11204 0.10621 0.0065 1.0000 0.2635
-9.000 -0.4307 0.10823 0.10247 0.0072 1.0000 0.2790
-8.750 -0.4290 0.10504 0.09937 0.0074 1.0000 0.2960
-8.500 -0.4386 0.10243 0.09689 0.0072 1.0000 0.3140
-8.250 -0.4043 0.09791 0.09238 0.0100 1.0000 0.3382
-8.000 -0.4239 0.09620 0.09082 0.0104 1.0000 0.3637
-7.750 -0.4084 0.09313 0.08783 0.0131 1.0000 0.3966
-7.500 -0.3697 0.08908 0.08382 0.0161 1.0000 0.4360
-7.250 -0.3476 0.08635 0.08116 0.0193 1.0000 0.4854
-7.000 -0.3326 0.08461 0.07951 0.0233 1.0000 0.5451
-6.000 -0.3169 0.05425 0.05043 -0.0109 0.9555 0.4305
-5.750 -0.3981 0.04417 0.03984 -0.0218 0.9342 0.3012
-5.500 -0.3984 0.03654 0.03067 -0.0262 0.9202 0.1610
-5.250 -0.4540 0.05084 0.04389 -0.0139 0.9429 0.1465
-5.000 -0.4062 0.04574 0.03800 -0.0173 0.9266 0.1218
-4.750 -0.3616 0.04249 0.03401 -0.0195 0.9090 0.1141
-4.500 -0.3203 0.03953 0.03056 -0.0212 0.8915 0.1129
-4.250 -0.2792 0.03696 0.02752 -0.0225 0.8739 0.1120
-4.000 -0.2386 0.03479 0.02491 -0.0233 0.8565 0.1129
-3.750 0.0825 0.02676 0.01968 -0.0548 0.8412 1.0000
-3.500 0.1019 0.02683 0.01926 -0.0537 0.8197 1.0000
-3.250 0.1217 0.02693 0.01896 -0.0527 0.8012 1.0000
-3.000 0.1423 0.02706 0.01875 -0.0519 0.7843 1.0000
-2.750 0.1638 0.02724 0.01861 -0.0515 0.7688 1.0000
-2.500 0.1859 0.02746 0.01857 -0.0512 0.7545 1.0000
-2.250 0.2079 0.02773 0.01859 -0.0508 0.7414 1.0000
-2.000 0.2291 0.02802 0.01863 -0.0502 0.7298 1.0000
-1.750 0.2514 0.02836 0.01876 -0.0499 0.7181 1.0000
-1.500 0.2749 0.02881 0.01905 -0.0501 0.7069 1.0000
-1.250 0.2960 0.02919 0.01921 -0.0492 0.6979 1.0000
-1.000 0.3196 0.02975 0.01966 -0.0497 0.6873 1.0000
-0.750 0.3419 0.03032 0.02008 -0.0495 0.6786 1.0000
-0.500 0.3644 0.03094 0.02060 -0.0495 0.6698 1.0000
-0.250 0.3865 0.03165 0.02119 -0.0495 0.6619 1.0000
0.000 0.4085 0.03241 0.02188 -0.0495 0.6535 1.0000
0.250 0.4297 0.03317 0.02254 -0.0492 0.6466 1.0000
0.500 0.4510 0.03428 0.02364 -0.0498 0.6387 1.0000
0.750 0.4716 0.03488 0.02412 -0.0487 0.6329 1.0000
1.000 0.4901 0.03650 0.02579 -0.0498 0.6249 1.0000
1.250 0.5095 0.03747 0.02670 -0.0493 0.6188 1.0000
1.500 0.5271 0.03877 0.02798 -0.0490 0.6132 1.0000
1.750 0.5396 0.04079 0.03005 -0.0494 0.6064 1.0000
2.000 0.5574 0.04181 0.03103 -0.0484 0.6010 1.0000
2.250 0.5672 0.04391 0.03315 -0.0481 0.5958 1.0000
2.500 0.5682 0.04672 0.03602 -0.0478 0.5906 1.0000
2.750 0.5786 0.04842 0.03771 -0.0466 0.5857 1.0000
3.000 0.5942 0.04974 0.03900 -0.0453 0.5813 1.0000
3.250 0.5737 0.05386 0.04318 -0.0438 0.5790 1.0000
3.500 0.5532 0.05743 0.04676 -0.0414 0.5778 1.0000
3.750 0.5320 0.06067 0.04998 -0.0383 0.5780 1.0000
4.000 0.5147 0.06344 0.05273 -0.0349 0.5798 1.0000
4.250 0.5103 0.06598 0.05526 -0.0328 0.5825 1.0000
5.500 0.3343 0.08034 0.06958 -0.0162 0.7030 1.0000
5.750 0.3398 0.08188 0.07110 -0.0145 0.6905 1.0000
6.000 0.3704 0.08527 0.07448 -0.0160 0.6821 1.0000
6.250 0.3711 0.08613 0.07533 -0.0135 0.6678 1.0000
6.500 0.3709 0.08732 0.07650 -0.0112 0.6547 1.0000
6.750 0.3812 0.08947 0.07866 -0.0103 0.6451 1.0000
7.250 0.3962 0.09289 0.08207 -0.0078 0.6216 1.0000
7.500 0.4099 0.09542 0.08462 -0.0074 0.6129 1.0000
7.750 0.4241 0.09750 0.08671 -0.0067 0.6008 1.0000
8.000 0.4186 0.09867 0.08787 -0.0045 0.5899 1.0000
8.250 0.4552 0.10311 0.09239 -0.0062 0.5821 1.0000
8.500 0.4408 0.10304 0.09230 -0.0032 0.5690 1.0000
8.750 0.4425 0.10498 0.09426 -0.0020 0.5601 1.0000
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Polar data table (+)
Polar graphs
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