EPPLER 396 AIRFOIL (e396-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 396 AIRFOIL (e396-il) Reynolds number: 50,000 Max Cl/Cd: 22.72 at α=11.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e396-il-50000-n5.txt Download as CSV file: xf-e396-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 396 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3085 0.13192 0.12539 -0.0443 1.0000 0.0534
-10.500 -0.3172 0.12993 0.12348 -0.0428 1.0000 0.0530
-10.250 -0.3264 0.12792 0.12157 -0.0414 1.0000 0.0524
-10.000 -0.3252 0.12408 0.11777 -0.0434 0.9972 0.0517
-9.750 -0.3168 0.11920 0.11290 -0.0477 0.9921 0.0510
-9.500 -0.3088 0.11457 0.10828 -0.0516 0.9866 0.0511
-9.000 -0.2940 0.10612 0.09982 -0.0588 0.9748 0.0538
-8.750 -0.2901 0.10135 0.09507 -0.0630 0.9688 0.0553
-8.500 -0.2900 0.09661 0.09037 -0.0666 0.9613 0.0562
-8.250 -0.2917 0.09177 0.08557 -0.0702 0.9540 0.0566
-8.000 -0.2954 0.08675 0.08059 -0.0741 0.9462 0.0567
-7.750 -0.3066 0.08176 0.07570 -0.0770 0.9365 0.0568
-7.500 -0.3119 0.07401 0.06796 -0.0848 0.9283 0.0569
-7.250 -0.3205 0.06439 0.05821 -0.0956 0.9184 0.0566
-7.000 -0.3263 0.05525 0.04855 -0.1052 0.9090 0.0577
-6.750 -0.3062 0.05067 0.04361 -0.1106 0.9038 0.0620
-6.500 -0.2864 0.04724 0.03979 -0.1137 0.8981 0.0669
-6.250 -0.2615 0.04278 0.03459 -0.1180 0.8926 0.0733
-6.000 -0.2294 0.04078 0.03223 -0.1208 0.8889 0.0824
-5.750 -0.2047 0.03922 0.03044 -0.1219 0.8838 0.0908
-5.500 -0.1772 0.03747 0.02827 -0.1234 0.8786 0.1010
-5.250 -0.1434 0.03618 0.02670 -0.1255 0.8750 0.1145
-5.000 -0.1142 0.03513 0.02538 -0.1266 0.8706 0.1275
-4.750 -0.0904 0.03455 0.02463 -0.1268 0.8647 0.1419
-4.500 -0.0576 0.03384 0.02383 -0.1283 0.8608 0.1584
-4.250 -0.0271 0.03338 0.02328 -0.1294 0.8568 0.1778
-4.000 -0.0055 0.03310 0.02288 -0.1289 0.8504 0.1947
-3.750 0.0269 0.03270 0.02238 -0.1302 0.8465 0.2179
-3.500 0.0582 0.03243 0.02195 -0.1312 0.8425 0.2420
-3.250 0.0781 0.03243 0.02192 -0.1304 0.8358 0.2617
-3.000 0.1110 0.03222 0.02160 -0.1316 0.8319 0.2889
-2.750 0.1395 0.03216 0.02151 -0.1320 0.8274 0.3139
-2.500 0.1605 0.03231 0.02158 -0.1314 0.8209 0.3370
-2.250 0.1935 0.03219 0.02141 -0.1324 0.8171 0.3663
-2.000 0.2185 0.03233 0.02148 -0.1323 0.8118 0.3934
-1.750 0.2412 0.03251 0.02168 -0.1318 0.8058 0.4193
-1.500 0.2745 0.03243 0.02155 -0.1327 0.8022 0.4519
-1.250 0.2936 0.03277 0.02192 -0.1317 0.7957 0.4791
-1.000 0.3192 0.03293 0.02209 -0.1315 0.7903 0.5111
-0.750 0.3522 0.03283 0.02201 -0.1322 0.7870 0.5482
-0.500 0.3654 0.03338 0.02264 -0.1302 0.7793 0.5788
-0.250 0.3923 0.03344 0.02275 -0.1299 0.7746 0.6199
0.000 0.4236 0.03325 0.02265 -0.1299 0.7717 0.6670
0.250 0.4289 0.03398 0.02350 -0.1267 0.7626 0.7077
0.500 0.4524 0.03379 0.02344 -0.1251 0.7586 0.7701
0.750 0.4568 0.03419 0.02400 -0.1212 0.7506 0.8526
1.000 0.4868 0.03424 0.02394 -0.1219 0.7453 1.0000
1.500 0.5373 0.03556 0.02492 -0.1229 0.7327 1.0000
1.750 0.5736 0.03574 0.02493 -0.1244 0.7292 1.0000
2.250 0.6183 0.03719 0.02619 -0.1241 0.7158 1.0000
2.500 0.6343 0.03820 0.02714 -0.1233 0.7077 1.0000
2.750 0.6620 0.03868 0.02756 -0.1236 0.7023 1.0000
3.000 0.6911 0.03909 0.02790 -0.1241 0.6976 1.0000
3.250 0.7050 0.04021 0.02900 -0.1230 0.6887 1.0000
3.500 0.7404 0.04027 0.02904 -0.1239 0.6853 1.0000
3.750 0.7474 0.04178 0.03055 -0.1222 0.6748 1.0000
4.000 0.7819 0.04183 0.03059 -0.1229 0.6712 1.0000
4.250 0.7892 0.04336 0.03215 -0.1212 0.6607 1.0000
4.500 0.8233 0.04338 0.03220 -0.1219 0.6569 1.0000
4.750 0.8303 0.04496 0.03382 -0.1202 0.6461 1.0000
5.000 0.8648 0.04489 0.03378 -0.1208 0.6423 1.0000
5.250 0.8713 0.04654 0.03548 -0.1191 0.6312 1.0000
5.500 0.9067 0.04633 0.03535 -0.1196 0.6276 1.0000
5.750 0.9125 0.04804 0.03713 -0.1179 0.6161 1.0000
6.000 0.9475 0.04775 0.03692 -0.1182 0.6122 1.0000
6.250 0.9548 0.04937 0.03863 -0.1166 0.6007 1.0000
6.500 0.9650 0.05081 0.04017 -0.1153 0.5900 1.0000
6.750 0.9986 0.05042 0.03991 -0.1153 0.5851 1.0000
7.000 1.0065 0.05202 0.04161 -0.1138 0.5734 1.0000
7.250 1.0405 0.05144 0.04115 -0.1136 0.5686 1.0000
7.500 1.0511 0.05278 0.04264 -0.1123 0.5571 1.0000
7.750 1.0607 0.05422 0.04420 -0.1109 0.5453 1.0000
8.000 1.0990 0.05294 0.04310 -0.1106 0.5410 1.0000
8.250 1.1069 0.05447 0.04476 -0.1090 0.5283 1.0000
8.500 1.1175 0.05574 0.04617 -0.1076 0.5160 1.0000
8.750 1.1601 0.05370 0.04437 -0.1071 0.5116 1.0000
9.250 1.1810 0.05599 0.04697 -0.1041 0.4854 1.0000
9.500 1.1946 0.05681 0.04795 -0.1026 0.4725 1.0000
9.750 1.2110 0.05726 0.04859 -0.1012 0.4597 1.0000
10.000 1.2300 0.05737 0.04891 -0.0998 0.4469 1.0000
10.250 1.2495 0.05736 0.04908 -0.0983 0.4332 1.0000
10.500 1.2670 0.05751 0.04941 -0.0968 0.4180 1.0000
10.750 1.2841 0.05769 0.04975 -0.0952 0.4016 1.0000
11.000 1.3035 0.05757 0.04976 -0.0936 0.3841 1.0000
11.250 1.3182 0.05801 0.05030 -0.0919 0.3647 1.0000
11.500 1.3247 0.05949 0.05187 -0.0904 0.3436 1.0000
11.750 1.3363 0.06031 0.05274 -0.0887 0.3213 1.0000
12.000 1.3405 0.06214 0.05460 -0.0872 0.2986 1.0000
12.250 1.3437 0.06418 0.05661 -0.0858 0.2762 1.0000
12.500 1.3449 0.06653 0.05892 -0.0846 0.2542 1.0000
12.750 1.3435 0.06940 0.06177 -0.0836 0.2335 1.0000
13.000 1.3408 0.07253 0.06487 -0.0828 0.2137 1.0000
13.250 1.3383 0.07573 0.06797 -0.0821 0.1956 1.0000
13.500 1.3341 0.07940 0.07168 -0.0818 0.1782 1.0000
13.750 1.3299 0.08317 0.07546 -0.0817 0.1621 1.0000
14.000 1.3261 0.08698 0.07927 -0.0817 0.1475 1.0000
14.250 1.3222 0.09093 0.08322 -0.0819 0.1341 1.0000
14.500 1.3183 0.09496 0.08725 -0.0822 0.1218 1.0000
14.750 1.3153 0.09890 0.09125 -0.0827 0.1112 1.0000
15.000 1.3124 0.10287 0.09518 -0.0833 0.1016 1.0000
15.250 1.3103 0.10702 0.09947 -0.0840 0.0923 1.0000
15.500 1.3091 0.11094 0.10346 -0.0847 0.0847 1.0000
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